CN103309319A - Distributive redundancy type automatic power distribution control system for airplane - Google Patents
Distributive redundancy type automatic power distribution control system for airplane Download PDFInfo
- Publication number
- CN103309319A CN103309319A CN201310216683XA CN201310216683A CN103309319A CN 103309319 A CN103309319 A CN 103309319A CN 201310216683X A CN201310216683X A CN 201310216683XA CN 201310216683 A CN201310216683 A CN 201310216683A CN 103309319 A CN103309319 A CN 103309319A
- Authority
- CN
- China
- Prior art keywords
- power controller
- power
- distribution
- controller
- bus
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
Landscapes
- Remote Monitoring And Control Of Power-Distribution Networks (AREA)
Abstract
The invention provides a distributive redundancy type automatic power distribution control system for an airplane. According to the distributive redundancy type automatic power distribution control system, a left power controller is used for monitoring and controlling a left alternating-current power distribution board, a left direct-current power distribution board and an emergency power distribution board through a digital and analog interface; a right power controller is used for monitoring and controlling a right alternating-current power distribution board, a right direct-current power distribution board and an emergency power distribution board through a digital and analog interface; the left and right power controllers feed an operating state of the system back to an upper computer through a 1553B communication data bus and a CAN (Controller Area Network) communication data bus; the left and right power controllers interact information of respective controlled power distribution boards through an ARINC429 bus; and an electric generator controller and a remote power controller transmit operating states of components respectively controlled by the electric generator controller and the remote power controller to the left and right power controllers. The distributive redundancy type automatic power distribution control system has the advantages that a health consultation function is achieved, the reliability and real-time property are improved; and power supply without interruption, fault-tolerant power supply and automatic management of load are realized by a power supply system.
Description
Technical field
The invention belongs to the automatic control technology field, especially relate to the automatic power distribution control system of distribution redundance type aircraft.
Background technology
The aircraft distribution network that Aircraft Automatic Electrical Power System mainly is made of each bus-bar, terminal and formed by the distribution control module that respective processor, controller consist of.Primary power distribution is the part from generator to the power supply bus-bar, and its control module is power controller PCU(Power Control Unit); Secondary power distribution is the part from the power supply bus-bar to distribution bus-bar and load, and its control module is long-range power supply unit RPDU(Remote Power Distribution Unit).
The automatic distribution control mode of aircraft is mainly centralized, distributed and concentrated distributed at present.The automatic power distribution control system of centralized only has a central processing unit, if central processing unit breaks down, whole aircraft power system can't normally be moved, so the reliability and stability of system are relatively poor; Do not have unified central processing unit in the distributed automatic power distribution control system, can't on system level, regulate and control aircraft power system, can produce the problem that is difficult to unified coordination between each long-range power supply unit; When concentrating dcs that complicated aircraft electrical network is carried out centralized control, because the huge and control algolithm complexity of system can cause real-time to reduce.In the general control mode of order, the control to emergent distribution center is difficult to accomplish the reliability guarantee of higher level.
Primary power distribution control module PCU is the core of Aircraft Automatic Electrical Power System, and it is seriously restricting the power supply reliability of aircraft distribution system to the control reliability of aircraft distribution network.And the automatic distribution control mode of redundant distributions formula all has vital role to the real-time of raising system control and the reliability of emergent distribution section control.
Summary of the invention
Technical matters to be solved by this invention is to overcome the deficiencies in the prior art, for the aircraft primary distribution network with left and right ac/dc distribution section and emergent distribution section, has proposed the automatic power distribution control system of distribution redundance type aircraft.Described system can carry out Redundant Control to emergent distribution section to the control that distributes of main ac/dc distribution section, has improved the power supply reliability of aircraft primary distribution network.
For solving the problems of the technologies described above, the technical solution adopted in the present invention is:
The automatic power distribution control system of distribution redundance type aircraft, it is characterized in that, described system comprises by host computer, left power controller, right power controller, left alternating-current distribution panel, right alternating-current distribution panel, left direct current panel, the right direct current of bus system connection joins single-deck, emergency switchboard, engine controller and remote power controller; Described left power controller is monitored respectively the running status of left alternating-current distribution panel, left direct current panel and emergency switchboard by numeral and analog interface, and respectively left alternating-current distribution panel, left direct current panel and emergency switchboard is controlled by network reconfiguration logical operation and overcurrent protection computing; Described right power controller is monitored respectively the running status that right alternating-current distribution panel, right direct current are joined single-deck and emergency switchboard by numeral and analog interface, and by network reconfiguration logical operation and overcurrent protection computing respectively to right alternating-current distribution panel, right direct current joins single-deck and emergency switchboard is controlled; Described host computer is controlled the state of left power controller, right power controller respectively, and shows respectively the status information of left power controller, right power controller;
Described left power controller, right power controller carry out Redundant Control to emergency switchboard jointly, and its method is as follows:
Determine respectively the priority of left power controller and right power controller; If the priority of right power controller is greater than the priority of left power controller, then by right power controller emergency switchboard is controlled, if right power controller is controlled unsuccessfully emergency switchboard, then take over right power controller by left power controller emergency switchboard is controlled, right power controller loses the control to emergency switchboard simultaneously;
If the priority of left power controller is greater than the priority of right power controller, then by left power controller emergency switchboard is controlled, if left power controller is controlled unsuccessfully emergency switchboard, then take over left power controller by right power controller emergency switchboard is controlled, left power controller loses the control to emergency switchboard simultaneously.
Described bus system comprises avionics system bus and electrical system bus; The avionics system bus comprises 1553B communication data bus and CAN communication data bus, and the electrical system bus comprises ARINC429 bus and RS485 communication data bus, CAN communication data bus; Host computer links to each other with left power controller, right power controller respectively by the avionics system bus; Pass through ARINC429 bus mutual separately running status and the self-monitoring result of the switchboard of controlling between left power controller and the right power controller, and realize the synchronous operation of left power controller and right power controller by the ARINC429 bus; Engine controller and remote power controller are distinguished left by RS485 communication data bus and CAN communication data bus, and power controller, right power controller feed back the separately running status of the parts of controlling.
Described left power controller is identical with right power controller functional module configuration, and described functional module comprises: power module, central processing unit and control circuit, memory module, communication interface circuit, digital interface circuit and analog interface circuit; Described power module provides power supply for power controller, the output of communication interface circuit, digital interface circuit and analog interface circuit is processed and controlled respectively to the information that described central processing unit and control circuit receive communication interface circuit, digital interface circuit and analog interface circuit respectively, and described memory module provides storage space and buffer memory for central processing unit and control circuit.
Described power module provides 2 power supplys, is respectively direct current bus-bar 28V power supply and accumulator 28V power supply in the aircraft distribution network; After the conversion of filtering and power module, power module is exported 4 road voltage sources, be respectively the 5V digital power, ± 15V analog power and 28V DC power power-supply.
Described central processing unit and control circuit are finished status information processing to the aircraft primary distribution network, communication information processing, control algolithm computing, control signal output and to self certainly detection.
Described memory module can staticly regularly be stored interior running status of the aircraft primary distribution network schedule time, the current running status of real-time storage aircraft primary distribution network.
Described communication interface circuit comprises two remaining 1553B communication interfaces, two remaining ARINC429 communication bus interface, dual-redundancy CAN communication interface and with the RS485 communication interface of remaining interface.
Described digital interface circuit realizes that power controller is to the processing of aircraft distribution network digital state signal and to the driving of contactor on the aircraft switchboard.
Described analog interface circuit realizes that power controller to the processing of aircraft distribution network simulating signal, is that 0V sends into central processing unit to 3V voltage with analog signal conversion.
The invention has the beneficial effects as follows: the present invention proposes the automatic power distribution control system of distribution redundance type aircraft, the left power controller of described system is by numeral and analog interface monitoring and control left alternating-current distribution panel, left direct current panel and emergency switchboard; Right power controller is by numeral and analog interface monitoring and control right alternating-current distribution panel, right direct current is joined single-deck and emergency switchboard; The state that left and right sides power controller moves to the host computer feedback system by 1553B communication data bus and CAN communication data bus; Pass through the mutual separately information of the switchboard of controlling of ARINC429 bus between the power controller of the left and right sides; Engine controller, remote power controller are by RS485 bus and the to the left and right power controller transmission of the CAN bus running status of the parts of controlling separately.The present invention has realized health diagnosis function, has improved reliability and real-time, and electric power system has realized that uninterrupted power supply, fault tolerant electrical power supply and load manage automatically.
Description of drawings
Fig. 1 is system architecture schematic diagram of the present invention.
Fig. 2 is systematic communication network schematic diagram of the present invention.
Fig. 3 is power controller hardware configuration schematic diagram of the present invention.
Fig. 4 is power controller master routine software flow schematic diagram of the present invention.
Fig. 5 is that power controller of the present invention is realized the subroutine software flow schematic diagram to main AC/DC switchboard distribution control.
Embodiment
Below in conjunction with accompanying drawing, the automatic power distribution control system of distribution redundance type aircraft that the present invention is proposed is elaborated:
As shown in Figure 1, the automatic power distribution control system of distribution redundance type aircraft of the present invention, system comprise a host computer, about two power controllers, four engine controllers, two remote power controllers and aircraft primary distribution network (comprising left alternating-current distribution panel, left direct current panel, right alternating-current distribution panel, right direct current panel and emergency switchboard).Left alternating-current distribution panel and left direct current panel are by left power controller monitoring and control, and right alternating-current distribution panel and right direct current panel are by right power controller monitoring and control, and emergency switchboard then left and right sides power controller all can monitor and control; The interface of power controller and switchboard comprises digital interface and analog interface.Left and right two power controllers with communicate by letter with host computer by 1553B bus and CAN bus, between two power controllers, and communicate by ARINC429, CAN and RS485 bus between power controller and engine controller, the remote power controller.
As shown in Figure 2, the communication network of the automatic power distribution control system of distribution redundance type aircraft is as follows: left and right two power controllers and upper strata avionics system bus have been connected with lower floor electrical system bus and have been connected, for upper strata avionics system bus, mainly communicate by letter with host computer by 1553B bus and CAN bus, for lower floor's electrical system bus, mainly be between two power controllers, and communicate by ARINC429, CAN and RS485 between power controller and engine controller, the remote power controller.The avionics system bus that power controller and host computer host computer adopt single channel CAN bus and 1553B bus to communicate by letter with host computer as power controller; The compound remaining that adopts single channel CAN bus and single channel RS485 bus to form between two power controllers and engine controller and the remote power controller is communicated by letter and is communicated; Adopt double channel A RINC429 communication to communicate between 2 power controllers.
As shown in Figure 3, left and right sides power controller is taked identical hardware configuration, comprising: power module, central processing unit and control circuit, memory module, communication interface circuit, digital interface circuit and analog interface circuit.The course of work of power controller is as follows: power controller receives various external status signals (such as contactor state, Bus Voltage and frequency etc.), and inner by certain control algolithm computing at processor, output distribution is the control signal of relevant contactor on the net, control signal is after driving circuit amplifies, control each contactor, thereby realize automatic distribution control and the fault isolation of aircraft power distribution network; In accepting state signal and the process that transmits control signal, PCU also needs constantly to communicate with host computer, another PCU and each engine controller GCU and RPDU, completion status monitoring and the functions such as feedback and reception instruction; For can after the electric network fault outage, finding out aircraft electric network fault reason by PCU, also need PCU upper with ROM (read-only memory), the working condition of storage aircraft electrical network in a period of time scope.
Described power module is finished the supply to the power controller electric energy.The power module input has 2 the tunnel, is respectively direct current bus-bar 28V power supply and accumulator 28V power supply in the aircraft distribution network.This power supply obtains 4 road power supply voltage signals after the conversion of filtering and power module, be respectively the 5V digital power, ± 15V analog power and 28VDC power power-supply.
Described central processing unit and control circuit are the cores of power controller, have finished status information processing to the aircraft primary distribution network, communication information processing, control algolithm computing, control signal output and to self certainly detection.Wherein central processing unit is the dsp chip TMS320F2812 of TI company, includes the relative program of whole control system operation; Control circuit mainly comprises CPLD(EPM7128S) and peripheral circuit, mainly realize address coding/decoding and correlation timing circuit by Digital Logic.
Described memory module can staticly regularly be stored aircraft primary distribution network running status within an hour, the current running status of dynamic real-time storage aircraft primary distribution network, and its core is Flash chips W F1M32B-G2UI3A.
Described communication interface circuit is realized the external communication interface of power controller, comprises two remaining 1553B communication interfaces, two remaining ARINC429 communication bus interface, dual-redundancy CAN communication interface and with the RS485 communication interface of remaining interface.
Described digital interface circuit realizes that power controller is to the hardware handles of aircraft distribution network digital state signal and to the driving of contactor on the aircraft switchboard.
Described analog interface circuit realizes that power controller to the hardware conditioning of aircraft distribution network simulating signal, is that 0 ~ 3V voltage is sent into central processing unit with analog signal conversion.
As shown in Figure 4, the main program flow of left and right power controller is identical, flow process is as follows: after system brings into operation, at first begin initialization and initial from detecting, self-monitoring result will be uploaded to host computer, normally then continue operation if certainly detect, otherwise just according to the Instruction Selection continuation of host computer or restart and reset; System enters normal operating phase afterwards, carries out information acquisition, and data are processed, the algorithm control algorithm, and the overcurrent protection computing, output control result also carries out message exchange and storage; Also need to carry out the process that On-line self-diagnosis is surveyed in system's normal course of operation, be used for judging whether the control output signal lost efficacy, find that fault then reports to the police to host computer immediately if On-line self-diagnosis is surveyed, and continue or reset according to the Instruction Selection of host computer.
In the described main program flow, obtain the current running status of electrical network and comprise the collection of digital signal, the collection of simulating signal and the reception of each bar communication bus data.
In the described main program flow, computing reconfiguration of electric networks steering logic process is the core in the software flow, about two power controller correspondences separately reconfiguration of electric networks algorithm.
As shown in Figure 5, left and right sides power controller is as follows to the distribute flow process of control of left ac/dc switchboard and right ac/dc switchboard separately: when distributing control, at first read the correlated digital/analog information on the aircraft switchboard, and carry out data and process, then carry out the network reconfiguration computing, draw the theoretic network reconfiguration result of calculation of aircraft distribution network
Net, when
NetRepresented to make corresponding branch road to connect at=1 o'clock; When
NetRepresented to make corresponding branch road to disconnect at=0 o'clock; Determine whether simultaneously to have branch road overcurrent on the switchboard, then begin to calculate the current protection time, if more than the overcurrent time remaining 2s, then carry out overcurrent protection, the overcurrent protection instruction that order is corresponding
Err=0, expression disconnects the overcurrent branch road.According to
NetAnd
ErrFinal opening on the synthetic switchboard/turn-off instruction
Cmd
Left and right power controller is as follows to the Redundant Control flow process of emergent distribution section: powering on when initial, RPCU at first controls emergent distribution section; After system was normal, RPCU can judge whether the relevant control instruction can realize by certainly detecting, and LPCU is in and monitors and Status of Backups simultaneously; Do not pass through from detecting in case the RPCU that is possessed of control power is relevant, then immediately control is licensed to LCPU, while self power out of hand; After being in the LPCU that monitors the status and receiving control, should control emergent distribution section immediately, prevent fault.
Claims (9)
1. the automatic power distribution control system of distribution redundance type aircraft, it is characterized in that, described system comprises by host computer, left power controller, right power controller, left alternating-current distribution panel, right alternating-current distribution panel, left direct current panel, the right direct current of bus system connection joins single-deck, emergency switchboard, engine controller and remote power controller; Described left power controller is monitored respectively the running status of left alternating-current distribution panel, left direct current panel and emergency switchboard by numeral and analog interface, and respectively left alternating-current distribution panel, left direct current panel and emergency switchboard is controlled by network reconfiguration logical operation and overcurrent protection computing; Described right power controller is monitored respectively the running status that right alternating-current distribution panel, right direct current are joined single-deck and emergency switchboard by numeral and analog interface, and by network reconfiguration logical operation and overcurrent protection computing respectively to right alternating-current distribution panel, right direct current joins single-deck and emergency switchboard is controlled; Described host computer is controlled the state of left power controller, right power controller respectively, and shows respectively the status information of left power controller, right power controller;
Described left power controller, right power controller carry out Redundant Control to emergency switchboard jointly, and its method is as follows:
Determine respectively the priority of left power controller and right power controller; If the priority of right power controller is greater than the priority of left power controller, then by right power controller emergency switchboard is controlled, if right power controller is controlled unsuccessfully emergency switchboard, then take over right power controller by left power controller emergency switchboard is controlled, right power controller loses the control to emergency switchboard simultaneously;
If the priority of left power controller is greater than the priority of right power controller, then by left power controller emergency switchboard is controlled, if left power controller is controlled unsuccessfully emergency switchboard, then take over left power controller by right power controller emergency switchboard is controlled, left power controller loses the control to emergency switchboard simultaneously.
2. the automatic power distribution control system of distribution redundance type aircraft according to claim 1 is characterized in that, described bus system comprises avionics system bus and electrical system bus; The avionics system bus comprises 1553B communication data bus and CAN communication data bus, and the electrical system bus comprises ARINC429 bus and RS485 communication data bus, CAN communication data bus; Host computer links to each other with left power controller, right power controller respectively by the avionics system bus; Pass through ARINC429 bus mutual separately running status and the self-monitoring result of the switchboard of controlling between left power controller and the right power controller, and realize the synchronous operation of left power controller and right power controller by the ARINC429 bus; Engine controller and remote power controller are distinguished left by RS485 communication data bus and CAN communication data bus, and power controller, right power controller feed back the separately running status of the parts of controlling.
3. the automatic power distribution control system of distribution redundance type aircraft according to claim 1, it is characterized in that, described left power controller is identical with right power controller functional module configuration, and described functional module comprises: power module, central processing unit and control circuit, memory module, communication interface circuit, digital interface circuit and analog interface circuit; Described power module provides power supply for power controller, the output of communication interface circuit, digital interface circuit and analog interface circuit is processed and controlled respectively to the information that described central processing unit and control circuit receive communication interface circuit, digital interface circuit and analog interface circuit respectively, and described memory module provides storage space and buffer memory for central processing unit and control circuit.
4. the automatic power distribution control system of distribution redundance type aircraft according to claim 3 is characterized in that, described power module provides 2 power supplys, is respectively direct current bus-bar 28V power supply and accumulator 28V power supply in the aircraft distribution network; After the conversion of filtering and power module, power module is exported 4 road voltage sources, be respectively the 5V digital power, ± 15V analog power and 28V DC power power-supply.
5. the automatic power distribution control system of distribution redundance type aircraft according to claim 3, it is characterized in that, described central processing unit and control circuit are finished status information processing to the aircraft primary distribution network, communication information processing, control algolithm computing, control signal output and to self certainly detection.
6. the automatic power distribution control system of distribution redundance type aircraft according to claim 3, it is characterized in that, described memory module can staticly regularly be stored interior running status of the aircraft primary distribution network schedule time, the current running status of real-time storage aircraft primary distribution network.
7. the automatic power distribution control system of distribution redundance type aircraft according to claim 3, it is characterized in that, described communication interface circuit comprises two remaining 1553B communication interfaces, two remaining ARINC429 communication bus interface, dual-redundancy CAN communication interface and with the RS485 communication interface of remaining interface.
8. the automatic power distribution control system of distribution redundance type aircraft according to claim 3 is characterized in that, described digital interface circuit realizes that power controller is to the processing of aircraft distribution network digital state signal and to the driving of contactor on the aircraft switchboard.
9. the automatic power distribution control system of distribution redundance type aircraft according to claim 3, it is characterized in that, described analog interface circuit realizes that power controller to the processing of aircraft distribution network simulating signal, is that 0V sends into central processing unit to 3V voltage with analog signal conversion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310216683.XA CN103309319B (en) | 2013-05-31 | 2013-05-31 | Distributive redundancy type automatic power distribution control system for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310216683.XA CN103309319B (en) | 2013-05-31 | 2013-05-31 | Distributive redundancy type automatic power distribution control system for airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103309319A true CN103309319A (en) | 2013-09-18 |
| CN103309319B CN103309319B (en) | 2015-10-28 |
Family
ID=49134644
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310216683.XA Expired - Fee Related CN103309319B (en) | 2013-05-31 | 2013-05-31 | Distributive redundancy type automatic power distribution control system for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103309319B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104914762A (en) * | 2015-05-15 | 2015-09-16 | 上海航空电器有限公司 | Civil aircraft distributed secondary distribution system architecture |
| CN105449842A (en) * | 2016-01-08 | 2016-03-30 | 清华大学 | Automotive redundant power supply |
| CN105549424A (en) * | 2016-01-06 | 2016-05-04 | 南京航空航天大学 | Wide-body passenger plane busbar power controller simulation system and method |
| CN109116245A (en) * | 2018-07-03 | 2019-01-01 | 深圳信果科技有限公司 | A kind of RPDU power supply monitoring system |
| CN110635515A (en) * | 2018-05-31 | 2019-12-31 | 上海航空电器有限公司 | Power input priority structure of generator bus bars of left channel and right channel of single-channel multi-electric-aircraft power supply system |
| CN111600635A (en) * | 2019-02-20 | 2020-08-28 | 霍尼韦尔有限公司 | Secondary power distribution system (SEPDS) for facilitating aircraft connectivity |
| CN115693928A (en) * | 2022-10-14 | 2023-02-03 | 哈尔滨工业大学 | ZYNQ-based airplane direct-current remote power distribution unit and power distribution control method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1967929A2 (en) * | 2007-03-05 | 2008-09-10 | Honeywell International Inc. | An intelligent aircraft secondary power distribution system that facilitates condition based maintenance |
| CN101752904A (en) * | 2009-12-23 | 2010-06-23 | 中国航空工业集团公司第六三一研究所 | Power supply system distributed controlling and managing subsystem computer |
| US20100231042A1 (en) * | 2009-03-16 | 2010-09-16 | Denis Vaughan Weale | Electrical power distribution |
| CN102270837A (en) * | 2011-07-28 | 2011-12-07 | 南京航空航天大学 | Network failure reconstruction method suitable for airplane distributed distribution system |
| CN102555811A (en) * | 2011-11-17 | 2012-07-11 | 株洲南车时代电气股份有限公司 | Power supply control method for electric locomotives and trains, device and system |
-
2013
- 2013-05-31 CN CN201310216683.XA patent/CN103309319B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1967929A2 (en) * | 2007-03-05 | 2008-09-10 | Honeywell International Inc. | An intelligent aircraft secondary power distribution system that facilitates condition based maintenance |
| US20100231042A1 (en) * | 2009-03-16 | 2010-09-16 | Denis Vaughan Weale | Electrical power distribution |
| CN101752904A (en) * | 2009-12-23 | 2010-06-23 | 中国航空工业集团公司第六三一研究所 | Power supply system distributed controlling and managing subsystem computer |
| CN102270837A (en) * | 2011-07-28 | 2011-12-07 | 南京航空航天大学 | Network failure reconstruction method suitable for airplane distributed distribution system |
| CN102555811A (en) * | 2011-11-17 | 2012-07-11 | 株洲南车时代电气股份有限公司 | Power supply control method for electric locomotives and trains, device and system |
Non-Patent Citations (3)
| Title |
|---|
| YANG SHANSHUI ET AL: "Novel Aircraft Electrical Power Distribution System Based on Distributed Computer", 《TRANSACTIONS OF NANJING UNIVERSITY OF AERONAUTICS & ASTRONAUTICS》 * |
| YANG SHANSHUI ET AL: "Redundancy Technology for Aircraft Multi-Channel DC Power Supply System", 《TRANSACTIONS OF NANJING UNIVERSITY OF AERONAUTICS & ASTRONAUTICS》 * |
| 孔令杰 等: "基于可靠性的航天器供配电***技术研究", 《江苏航空》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104914762A (en) * | 2015-05-15 | 2015-09-16 | 上海航空电器有限公司 | Civil aircraft distributed secondary distribution system architecture |
| CN105549424A (en) * | 2016-01-06 | 2016-05-04 | 南京航空航天大学 | Wide-body passenger plane busbar power controller simulation system and method |
| CN105449842A (en) * | 2016-01-08 | 2016-03-30 | 清华大学 | Automotive redundant power supply |
| CN105449842B (en) * | 2016-01-08 | 2017-09-15 | 清华大学 | A kind of automobile-used remaining power supply |
| CN110635515A (en) * | 2018-05-31 | 2019-12-31 | 上海航空电器有限公司 | Power input priority structure of generator bus bars of left channel and right channel of single-channel multi-electric-aircraft power supply system |
| CN110635515B (en) * | 2018-05-31 | 2023-08-25 | 上海航空电器有限公司 | Power input priority structure for bus bars of left and right channel generator of aircraft power supply system |
| CN109116245A (en) * | 2018-07-03 | 2019-01-01 | 深圳信果科技有限公司 | A kind of RPDU power supply monitoring system |
| CN111600635A (en) * | 2019-02-20 | 2020-08-28 | 霍尼韦尔有限公司 | Secondary power distribution system (SEPDS) for facilitating aircraft connectivity |
| CN115693928A (en) * | 2022-10-14 | 2023-02-03 | 哈尔滨工业大学 | ZYNQ-based airplane direct-current remote power distribution unit and power distribution control method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103309319B (en) | 2015-10-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103309319A (en) | Distributive redundancy type automatic power distribution control system for airplane | |
| CN110361979B (en) | Safety computer platform in railway signal field | |
| CN106375072B (en) | Redundancy control method for locomotive communication network | |
| CN104238435A (en) | Triple-redundancy control computer and fault-tolerant control system | |
| CN103176870B (en) | Multi-mode information interaction redundancy safety computer platform | |
| CN102856971B (en) | A kind of DC power system and method realizing multimachine monitoring | |
| CN102320318B (en) | MVB (multifunction vehicle bus) dual-redundancy car door network system | |
| CN105739299A (en) | Control device based on double 2-vote-2 safety redundancy system | |
| CN105187248A (en) | Redundancy switching system | |
| CN102331786A (en) | Dual-computer cold-standby system of attitude and orbit control computer | |
| CN103853622A (en) | Control method of dual redundancies capable of being backed up mutually | |
| CN204340923U (en) | A kind of whole-control system and there is its vehicle | |
| CN101752904B (en) | Power supply system distributed controlling and managing subsystem computer | |
| CN102624075B (en) | Multimachine parallel connection method and scheme of modular UPS (uninterrupted power supply) system | |
| CN102508746A (en) | Management method for triple configurable fault-tolerant computer system | |
| CN202421819U (en) | Triple redundancy analog output module for DCS (Distributed Control System) | |
| CN105045181A (en) | Overall redundant architecture of PAS 100 control system | |
| CN105529822A (en) | Redundancy control protection system | |
| CN210129215U (en) | Dual-redundancy electromechanical management computer architecture | |
| CN111261458B (en) | Contactor control method adopting non-similar dual processors in aviation power distribution system | |
| CN104691761A (en) | Multi-mode hybrid power supply system and method for ICP (integrated core processor) | |
| CN110196564A (en) | A kind of anti-single particle radiation smoothly switches dual-computer redundancy distribution system | |
| CN112445751B (en) | Computer host interface board suitable for multi-mode redundant system | |
| CN103472746B (en) | The redundancy control method of dual master control equipment and dual master control equipment | |
| CN107831686A (en) | A kind of Digitizing And Control Unit for satellite power supply controller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151028 |