CN105549439A - Airplane seat power supply system - Google Patents
Airplane seat power supply system Download PDFInfo
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- CN105549439A CN105549439A CN201511030681.7A CN201511030681A CN105549439A CN 105549439 A CN105549439 A CN 105549439A CN 201511030681 A CN201511030681 A CN 201511030681A CN 105549439 A CN105549439 A CN 105549439A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25314—Modular structure, modules
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Remote Monitoring And Control Of Power-Distribution Networks (AREA)
Abstract
The invention relates to an airplane seat power supply system. The system comprises a motherboard, a processor board, multiple management boards, a power supply input interface and at least one power supply output interface, wherein the motherboard is electrically connected with the power supply input interface and the processor board, the motherboard comprises multiple slots, the multiple management boards are detachably electrically connected with the motherboard through the slots, each management board comprises multiple function modules for power supply detection, the management boards are electrically connected with the power supply output interface, and the processor board comprises a micro-control module. According to the airplane seat power supply system provided by the invention, the multiple management boards are connected with the motherboard trough the slots in the motherboard, one power supply of an airplane power network is distributed into multiple power supplies via the motherboard for going into the multiple mother boards, and the detection of detecting the power supplies distributed by the motherboard can be realized through the multiple function modules on the management boards. The airplane seat power supply system provided by the invention is low in manufacturing cost and facilitates later maintenance and function expansion through a modular design.
Description
Technical field
The present invention relates to avionic device field, in particular to a kind of aircraft seat power-supply system.
Background technology
At present, the midfrequent AC power supply that the airplane power source that aircraft uses is 115V/400Hz, provides primarily of aircraft electrical network.Now, passenger's airplane generally all carries with electronic equipment, as mobile phone, panel computer etc., but the midfrequent AC power supply of 115V/400Hz can not be directly the electronic equipment charging of passenger, so there is aircraft seat power supply, specially the electric network source of aircraft is converted to the power supply being applicable to electronic equipment charging by inverter circuit.In order to ensure the normal work of aircraft seat power supply, by aircraft seat power-supply system, aircraft electric network source seat power module be can be introduced and Power convert and the working state real-time monitoring to seat power module carried out, existing aircraft seat power supply cost of manufacture is high, once break down, large area is needed to change parts, and the replacement cycle of parts is long, the maintenance for the later stage causes larger difficulty, and the use cost of client is high.Be badly in need of the aircraft seat power-supply system that a kind of cost is low, the later maintenance cycle is short, powerful on the market.
Summary of the invention
In view of this, the object of the embodiment of the present invention is to provide a kind of aircraft seat power-supply system, to improve above-mentioned problem.
The present invention is achieved in that a kind of aircraft seat power-supply system, for controlling aircraft seat power module, described aircraft seat power-supply system comprises motherboard, processor plate, multiple management board, power input interface and multiple power output interface, described power input interface is electrically connected with described motherboard, described motherboard is electrically connected with described processor plate, described motherboard comprises multiple slot, described multiple management board is removably electrically connected with described motherboard respectively by a described slot, each described management board includes multiple functional module for detecting power supply, described multiple management board is electrically connected with a described power output interface respectively, described processor plate comprises micro-control module, wherein,
Described power input interface is for introducing aircraft electric network source;
Described motherboard is used for described aircraft electric network source to be dispensed to described multiple management board;
Described management board is for monitoring the aircraft electric network source of described motherboard distribution and exporting described aircraft electric network source to described power output interface;
The aircraft electric network source that described power output interface is used for described management board to export is delivered to aircraft seat power module;
Described processor plate monitors described motherboard and described management board by described micro-control module.
Preferably; described management board also comprises the first switch; described management board is connected with described power output interface by described first switch; described micro-control module and described first switch and multiple functional module are all electrically connected; described functional module comprises input electric cur-rent measure module, leakage protection module, output electric current measure module and power conditioning module; wherein
The first current value that described input electric cur-rent measure module inputs to described management board for detecting described motherboard, and the first current value detected is sent to described micro-control module, described micro-control module is used for this first current value and the first current value preset to compare, when the first current value that input electric cur-rent measure module detects exceedes the first default current value, described micro-control module sends the first enable command to described first switch, and described second switch is used for disconnecting when receiving this first enable command;
Described leakage protection module is used for the leakage current value of detection management plate to ground, and the leakage current value of detection is sent to described micro-control module, described micro-control module is used for this leakage current value and the leakage current value preset to compare, when the leakage current value that leakage protection module detects exceedes default leakage current value, described micro-control module sends the second enable command to described first switch, and described first switch is used for disconnecting when receiving this second enable command;
Described output electric current measure module outputs to the second current value of described power output interface for detecting described management board, and the second current value detected is sent to described micro-control module, described micro-control module is used for this second current value and the second current value preset to compare, when the second current value that output electric current measure module detects exceedes the second default current value, described micro-control module sends to described power conditioning module and drives order, described power conditioning module be used for according to this driving order by power output interface to aircraft seat power module outputs level signals, to limit the use power of described aircraft seat power module.
Preferably, described management board also comprises fuse, and aircraft electric network source is sent into described management board by described fuse by described motherboard, and described fuse is used for fusing when the first current value exceedes the first default current value.
Preferably, described aircraft seat power-supply system also comprises alterating and direct current source module, described motherboard is also for being dispensed to described alterating and direct current source module by described aircraft electric network source, described alterating and direct current source module is used for the AC power of aircraft electrical network to be converted to direct supply, and this direct supply is the accessory power supply of described aircraft seat power-supply system work.
Preferably, described motherboard also comprises input voltage measurement module and second switch, described micro-control module and described input voltage measurement module and described second switch are all electrically connected, described power input interface is by one end of second switch described in described input voltage measurement model calling, the other end of described second switch connects described multiple slot and alterating and direct current source module respectively, wherein
The magnitude of voltage of detection for detecting the voltage of the aircraft electric network source of described power input interface introducing, and is sent to described micro-control module by described input voltage measurement module;
The magnitude of voltage that described micro-control module sends for receiving described voltage detection module, this magnitude of voltage and the range of voltage values preset are compared, when the magnitude of voltage that voltage input detection module sends belongs to default range of voltage values, described micro-control module sends the 3rd enable command to described second switch, when the magnitude of voltage that input voltage measurement module sends exceeds default range of voltage values, described micro-control module sends the 4th enable command to described second switch;
Described second switch is used for closing when receiving the 3rd enable command that described micro-control module sends, and for disconnecting when receiving the 4th enable command that described micro-control module sends.
Preferably, described aircraft seat power-supply system also comprises temperature sensor, and described temperature sensor is electrically connected with described micro-control module, wherein,
The temperature information of sensing for sensing the temperature information of described aircraft seat power-supply system inside, and is sent to described micro-control module by described temperature sensor;
Described micro-control module is used for this temperature information and the temperature information preset to compare, and when the temperature information that described temperature sensor senses arrives is higher than the temperature information preset, described micro-control module sends the 5th enable command to described second switch;
Described second switch is used for disconnecting when receiving the 5th enable command.
Preferably, described motherboard also comprises filtration module, and described input voltage measurement module is connected to described second switch by described filtration module, and described filtration module is used for the clutter of filtering aircraft electric network source.
Preferably, described aircraft seat power-supply system also comprises state display module, and described state display module is for showing the duty of described aircraft seat management equipment.
Preferably, described management board also comprises selftest module, and described selftest module is used for detecting the duty of the functional module of described management board, and the result of detection is shown by described display module.
Preferably, described aircraft seat power-supply system also comprises ether web plate, and described aircraft seat power-supply system sets up communication by described ether web plate and the seat power module of aircraft and the entertainment systems of aircraft.
Multiple management boards of aircraft seat power-supply system provided by the invention are connected with motherboard by the slot on motherboard, the power supply of aircraft electrical network is assigned as multichannel through motherboard, enter multiple management board, by the multiple Implement of Function Modules on management board to the measuring ability of the power supply that motherboard distributes.Aircraft seat power-supply system low cost of manufacture provided by the invention, modular design is beneficial to later maintenance and Function Extension.
For making above-mentioned purpose of the present invention, feature and advantage become apparent, preferred embodiment cited below particularly, and coordinate appended accompanying drawing, be described in detail below.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme of the embodiment of the present invention, be briefly described to the accompanying drawing used required in embodiment below, be to be understood that, the following drawings illustrate only some embodiment of the present invention, therefore the restriction to scope should be counted as, for those of ordinary skill in the art, under the prerequisite not paying creative work, other relevant accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 shows the block diagram of the functional module framework of a kind of aircraft seat power-supply system that first embodiment of the invention provides.
Fig. 2 shows the block diagram of the functional module framework of a kind of aircraft seat power-supply system that second embodiment of the invention provides.
Fig. 3 shows the block diagram of the functional module framework of a kind of aircraft seat power-supply system that third embodiment of the invention provides.
Wherein, Reference numeral gathers as follows: motherboard 110, alterating and direct current source module 111, input voltage measurement module 112, second switch 113, filtration module 114, processor plate 120, micro-control module 121, management board 130, input electric cur-rent measure module 131, leakage protection module 132, output electric current measure module 133, power conditioning module 134, first switch 135, fuse 136, selftest module 137, power input interface 140, power output interface 150, temperature sensor 160, ether web plate 170, display module 180.
Embodiment
In order to ensure the normal work of aircraft seat power module, embodiments providing a kind of aircraft seat power-supply system, aircraft electric network source can be carried out hyperchannel distribution, and inspection monitoring is carried out to the power supply of each passage.
Below in conjunction with accompanying drawing in the embodiment of the present invention, be clearly and completely described the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.The assembly of the embodiment of the present invention describing and illustrate in usual accompanying drawing herein can be arranged with various different configuration and design.Therefore, below to the detailed description of the embodiments of the invention provided in the accompanying drawings and the claimed scope of the present invention of not intended to be limiting, but selected embodiment of the present invention is only represented.Based on embodiments of the invention, the every other embodiment that those skilled in the art obtain under the prerequisite not making creative work, all belongs to the scope of protection of the invention.
First embodiment
Referring to Fig. 1, is the functional module framework schematic diagram of the aircraft seat power-supply system 100 that the embodiment of the present invention provides.The aircraft seat power-supply system 100 that the embodiment of the present invention provides comprises motherboard 110, processor plate 120, multiple management board 130, power input interface 140 and multiple power output interface 150.Power input interface 140 and processor plate 120 are all electrically connected with motherboard 110, motherboard 110 comprises multiple slot, multiple management board 130 is removably electrically connected with motherboard 110 respectively by a slot, each management board 130 all arranges multiple functional module, described functional module is used for the power supply on detection management plate 130, the plurality of management board 130 is electrically connected with a power output interface 150 respectively, and processor plate 120 comprises micro-control module 121.
Wherein, power input interface 140 is for introducing aircraft electric network source.Motherboard 110 is for being dispensed to multiple management board 130 by described aircraft electric network source.Management board 130 is for monitoring the aircraft electric network source of described motherboard 110 distribution and exporting described aircraft electric network source to power output interface 150.Power output interface 150 is delivered to aircraft seat power module for the aircraft electric network source exported by management board 130.Processor plate 120 monitors motherboard 110 and management board 130 by micro-control module 121.
After the electric network source of aircraft enters motherboard 110 by power input interface 140, distribute through motherboard 110, enter in multiple management board 130, the power supply of aircraft electrical network is the three-phase alternating current potential source of 115V/400Hz, the single-phase alternating-current voltage source in Wei tri-tunnel is exported through each management board 130, to meet the use standard of electronic equipment, the alternating-current voltage source that each road is single-phase is provided with functional module.In the aircraft seat power-supply system 100 that the present embodiment provides, the quantity of management board 130 is preferably 5, to adapt to the existing equipment of current aerospace industry, but on the quantity of management board 130 and motherboard 110, the quantity of slot can freely be arranged, and the embodiment of the present invention does not limit this.Because management board 130 is arranged on motherboard 110 by the mode of grafting, management board 130 carries out monitoring management by multiple functional module to power supply, is convenient to the maintenance in later stage, reduces production cost.
In the aircraft seat power-supply system 100 that the present embodiment provides, management board 130 comprises the first switch 135.Functional module on management board 130 comprises input electric cur-rent measure module 131, leakage protection module 132, output electric current measure module 133 and power conditioning module 134.Described micro-control module 121 is all electrically connected with described first switch 135, input electric cur-rent measure module 131, leakage protection module 132, output electric current measure module 133 and power conditioning module 134.
Wherein, the first current value that input electric cur-rent measure module 131 inputs to management board 130 for detecting motherboard 110, and the first current value detected is sent to micro-control module 121.After micro-control module 121 receives this first current value, this first current value and the first current value preset are compared.When the first current value that input electric cur-rent measure module 131 detects exceedes the first default current value, micro-control module sends the first enable command to the first switch 135.First switch 135 disconnects when receiving this first enable command, cuts off the output of this management board 130 to aircraft seat power module, with prevent the electric current on this management board 130 excessive or there is short circuit time burn out aircraft seat power module.
The leakage current value of detection for the leakage current value of detection management plate 130 to ground, and is sent to micro-control module 121 by leakage protection module 132.After micro-control module 121 receives this leakage current value, this leakage current value and the leakage current value preset are compared.When the leakage current value that leakage protection module 132 detects exceedes default leakage current value, micro-control module 121 sends the second enable command to the first switch 135.First switch 135 disconnects when receiving this second enable command, to cut off the output of this management board 130 to aircraft seat power module.
Output electric current measure module 133 outputs to the second current value of power output interface for detection management plate 130, and the second current value detected is sent to micro-control module 121, micro-control module 121 is for comparing this second current value and the second current value preset, when the second current value that output electric current measure module 133 detects exceedes the second default current value, micro-control module 121 sends to power conditioning module 134 and drives order, power conditioning module 134 for according to this driving order by power output interface 150 to aircraft seat power module outputs level signals, to regulate the use power of described aircraft seat power module.
Aircraft electric network source is dispensed to multiple management board 130 by motherboard 110 by the aircraft seat power-supply system 100 that the embodiment of the present invention provides, the aircraft electric network source of three-phase is converted to the single-phase voltage source in three tunnels by each management board 130, transfers to aircraft seat power module to carry out Power convert by power output interface 150.Simultaneously, carry out detecting in real time to the power supply on management board 130 by the functional module on management board 130 and to monitor and the micro-control module 121 testing result being sent to processor plate 120 is analyzed, micro-control module 121 makes corresponding instruction after analyzing, and guarantees the normal work of whole aircraft seat power-supply system 100.Slot by motherboard 110 between management board 130 with motherboard 110 realizes being electrically connected, be beneficial to installation and maintenance, management board 130 is by the monitoring of multiple Implement of Function Module to power supply, and modular design is beneficial to maintenance and the Function Extension in later stage, and saves maintenance cost and production cost.
Second embodiment
Referring to Fig. 2, is the functional module framework schematic diagram of the aircraft seat power-supply system 200 that the embodiment of the present invention provides.The present embodiment is roughly the same with the first embodiment; distinctive points is: described management board 130 also comprises fuse 136; aircraft electric network source is sent into described management board 130 by described fuse 136 by motherboard 110; described fuse 136 is for fusing when the first current value exceedes the load current value of fuse 136; realize overcurrent or short-circuit protection, guarantee the normal work of whole management board 130.
In addition, the improvement of the present embodiment is also: described aircraft seat power-supply system 200 also comprises alterating and direct current source module 111, aircraft electric network source is dispensed to described alterating and direct current source module 111 by described motherboard 110, to make described alterating and direct current source module 111 that the AC power of aircraft electrical network is converted to direct supply, this direct supply provides the accessory power supply of work for aircraft seat power-supply system 200.The position that described alterating and direct current source module 111 is arranged is determined according to factors such as product actual look, size performances.Motherboard 110 also comprises input voltage measurement module 112 and second switch 113.The micro-control module 121 of processor plate 120 is all electrically connected with described input voltage measurement module 112 and second switch 113.Described power input interface 140 connects one end of described second switch 113 by input voltage measurement module 112, and the other end of described second switch 113 connects described multiple slot and alterating and direct current source module 111 respectively.
Input voltage measurement module 112 is for detecting the voltage of the aircraft electric network source of described power input interface introducing, and the magnitude of voltage of detection is sent to micro-control module 121, after micro-control module 121 receives the magnitude of voltage of described input voltage measurement module 112 transmission, this magnitude of voltage and the range of voltage values preset are compared.When the magnitude of voltage that input voltage measurement module 112 sends is in the range of voltage values preset, described micro-control module 121 sends the 3rd enable command to described second switch 113, and second switch 113 is closed when receiving the 3rd enable command that described micro-control module 121 sends.When the magnitude of voltage that input voltage measurement module 112 sends exceeds default range of voltage values, described micro-control module 121 sends the 4th enable command to described second switch 113, and second switch 113 disconnects when receiving the 4th enable command that described micro-control module 121 sends.
Input voltage measurement module 112 detects the power supply that power input interface 140 is introduced in real time, when aircraft power network fluctuation is larger, magnitude of voltage exceedes the normal value situation of overvoltage (under-voltage or), namely micro-control module 121 controls second switch 113 and disconnects, effectively reduce aircraft network load, prevent the electronic devices and components in aircraft seat power-supply system 200 from receiving damage because the voltage stress born exceedes the normal scope of application simultaneously.
In addition, in order to protect the use safety of aircraft seat power-supply system 200 further, aircraft seat power-supply system 200 is also provided with temperature sensor 160, and this temperature sensor 160 is electrically connected with described micro-control module 121.The temperature information of sensing for sensing the temperature information of aircraft seat power-supply system 200 inside, and is sent to micro-control module 121 by described temperature sensor 160.This temperature information and the temperature information preset compare by described micro-control module 121, when the temperature information that temperature sensor 160 senses is higher than the temperature information preset, micro-control module 121 sends the 5th enable command to second switch 113, and second switch 113 disconnects when receiving the 5th enable command.Temperature sensor 160 can be arranged on the optional position of aircraft seat power-supply system 200 inside, is such as arranged on motherboard 110, or on management board 130, the embodiment of the present invention does not limit this.The setting of temperature sensor 160, the too high initiation fire of the temperature of aircraft seat power-supply system 200 can be prevented, reduce temperature to the impact of aircraft seat power-supply system 200 reliability, avoid the too high damage causing aircraft seat power-supply system 200 internal power device of Yin Wendu.
3rd embodiment
Please refer to Fig. 3, is the functional module framework schematic diagram of the aircraft seat power-supply system 300 that the embodiment of the present invention provides.The embodiment of the present invention is roughly the same with the second embodiment, and distinctive points is: motherboard 110 also comprises filtration module 114, and described input voltage measurement module 112 is connected to described second switch 113 by described filtration module 114.Filtration module 114 is for the clutter of filtering aircraft electric network source.The high-frequency impulse of filtration module 114 filtering aircraft electrical network is to the Conduction Interference of aircraft seat power-supply system 300, reduce aircraft seat power-supply system 300 pairs of aircraft power supply radiation interference, filtering electrical network medium-high frequency clutter and in the same way interference current well, electromagnetic radiation aircraft seat power-supply system 300 produced reduces, and prevents from causing harmful effect to human body or other equipment.
The improvement of the present embodiment is also: aircraft seat power-supply system 300 also comprises ether web plate 170 and display module 180, and described aircraft seat power-supply system 300 sets up communication by described ether web plate 170 with the seat power module of aircraft and the entertainment systems of aircraft.Display module 180 for showing the duty of described aircraft seat management equipment 300, as power input interface 140 introduce the state of each phase of power supply, the output state etc. of each management board 130.The display mode of display module 180 can be realized by pilot lamp or display screen, and the embodiment of the present invention does not limit this.Described management board 130 also comprises selftest module 137, and described selftest module 137 detects for the duty of the functional module to described management board 130, and the result of detection is shown by described display module 180.When selftest module 137 detects that a certain functional module occurs abnormal, signal can be sent to micro-control module 121, after micro-control module 121 judges according to this signal, send corresponding control command to display module 180, make display module 180 show corresponding information.Such as; when selftest module 137 detects that the defencive function of leakage protection module 132 occurs extremely; selftest module 137 sends signal to micro-control module 121; micro-control module 121 judges according to this signal; send control command to display module 180, the display creepage protection function controlling display module 180 is abnormal.In process of self-test, display module 180 shows aircraft seat power-supply system 300 and is in self-inspection, and after self-inspection terminates, display module 180 shows the result of aircraft seat power-supply system 300 self-inspection.The information that selftest module 137 detects is sent to airplane entertainment systems through micro-control module 121 by ether web plate 170, can realize the monitoring to aircraft seat power-supply system 300 and warning function.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; change can be expected easily or replace, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should described be as the criterion with the protection domain of claim.
Claims (10)
1. an aircraft seat power-supply system, for controlling aircraft seat power module, it is characterized in that, described aircraft seat power-supply system comprises motherboard, processor plate, multiple management board, power input interface and multiple power output interface, described power input interface is electrically connected with described motherboard, described motherboard is electrically connected with described processor plate, described motherboard comprises multiple slot, described multiple management board is removably electrically connected with described motherboard respectively by a described slot, each described management board includes multiple functional module for detecting power supply, described multiple management board is electrically connected with a described power output interface respectively, described processor plate comprises micro-control module, wherein,
Described power input interface is for introducing aircraft electric network source;
Described motherboard is used for described aircraft electric network source to be dispensed to described multiple management board;
Described management board is for monitoring the aircraft electric network source of described motherboard distribution and exporting described aircraft electric network source to described power output interface;
The aircraft electric network source that described power output interface is used for described management board to export is delivered to aircraft seat power module;
Described processor plate monitors described motherboard and described management board by described micro-control module.
2. aircraft seat power-supply system according to claim 1; it is characterized in that; described management board also comprises the first switch; described management board is connected with described power output interface by described first switch; described micro-control module and described first switch and multiple functional module are all electrically connected; described functional module comprises input electric cur-rent measure module, leakage protection module, output electric current measure module and power conditioning module, wherein
The first current value that described input electric cur-rent measure module inputs to described management board for detecting described motherboard, and the first current value detected is sent to described micro-control module, described micro-control module is used for this first current value and the first current value preset to compare, when the first current value that input electric cur-rent measure module detects exceedes the first default current value, described micro-control module sends the first enable command to described first switch, and described second switch is used for disconnecting when receiving this first enable command;
Described leakage protection module is used for the leakage current value of detection management plate to ground, and the leakage current value of detection is sent to described micro-control module, described micro-control module is used for this leakage current value and the leakage current value preset to compare, when the leakage current value that leakage protection module detects exceedes default leakage current value, described micro-control module sends the second enable command to described first switch, and described first switch is used for disconnecting when receiving this second enable command;
Described output electric current measure module outputs to the second current value of described power output interface for detecting described management board, and the second current value detected is sent to described micro-control module, described micro-control module is used for this second current value and the second current value preset to compare, when the second current value that output electric current measure module detects exceedes the second default current value, described micro-control module sends to described power conditioning module and drives order, described power conditioning module be used for according to this driving order by power output interface to aircraft seat power module outputs level signals, to limit the use power of described aircraft seat power module.
3. aircraft seat power-supply system according to claim 2, it is characterized in that, described management board also comprises fuse, and aircraft electric network source is sent into described management board by described fuse by described motherboard, and described fuse is used for fusing when the first current value exceedes the first default current value.
4. aircraft seat power-supply system according to claim 1, it is characterized in that, also comprise alterating and direct current source module, described motherboard is also for being dispensed to described alterating and direct current source module by described aircraft electric network source, described alterating and direct current source module is used for the AC power of aircraft electrical network to be converted to direct supply, and this direct supply is the accessory power supply of described aircraft seat power-supply system work.
5. aircraft seat power-supply system according to claim 1, it is characterized in that, described motherboard also comprises input voltage measurement module and second switch, described micro-control module and described input voltage measurement module and described second switch are all electrically connected, described power input interface is by one end of second switch described in described input voltage measurement model calling, the other end of described second switch connects described multiple slot and alterating and direct current source module respectively, wherein
The magnitude of voltage of detection for detecting the voltage of the aircraft electric network source of described power input interface introducing, and is sent to described micro-control module by described input voltage measurement module;
The magnitude of voltage that described micro-control module sends for receiving described voltage detection module, this magnitude of voltage and the range of voltage values preset are compared, when the magnitude of voltage that input voltage measurement module sends belongs to default range of voltage values, described micro-control module sends the 3rd enable command to described second switch, when the magnitude of voltage that input voltage measurement module sends exceeds default range of voltage values, described micro-control module sends the 4th enable command to described second switch;
Described second switch is used for closing when receiving the 3rd enable command that described micro-control module sends, and for disconnecting when receiving the 4th enable command that described micro-control module sends.
6. aircraft seat power-supply system according to claim 5, is characterized in that, also comprise temperature sensor, and described temperature sensor is electrically connected with described micro-control module, wherein,
The temperature information of sensing for sensing the temperature information of described aircraft seat power-supply system inside, and is sent to described micro-control module by described temperature sensor;
Described micro-control module is used for this temperature information and the temperature information preset to compare, and when the temperature information that described temperature sensor senses arrives is higher than the temperature information preset, described micro-control module sends the 5th enable command to described second switch;
Described second switch is used for disconnecting when receiving the 5th enable command.
7. aircraft seat power-supply system according to claim 6, it is characterized in that, described motherboard also comprises filtration module, and described input voltage measurement module is connected to described second switch by described filtration module, and described filtration module is used for the clutter of filtering aircraft electric network source.
8. aircraft seat power-supply system according to claim 1, is characterized in that, also comprise state display module, and described state display module is for showing the duty of described aircraft seat management equipment.
9. aircraft seat power-supply system according to claim 8, it is characterized in that, described management board also comprises selftest module, and described selftest module is used for detecting the duty of the functional module of described management board, and the result of detection is shown by described display module.
10. aircraft seat power-supply system according to claim 1, is characterized in that, also comprises ether web plate, and described aircraft seat power-supply system sets up communication by described ether web plate and the seat power module of aircraft and the entertainment systems of aircraft.
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Application publication date: 20160504 |