CN103309319B - Distributive redundancy type automatic power distribution control system for airplane - Google Patents
Distributive redundancy type automatic power distribution control system for airplane Download PDFInfo
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- CN103309319B CN103309319B CN201310216683.XA CN201310216683A CN103309319B CN 103309319 B CN103309319 B CN 103309319B CN 201310216683 A CN201310216683 A CN 201310216683A CN 103309319 B CN103309319 B CN 103309319B
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Abstract
The present invention proposes distributive redundancy type automatic power distribution control system for airplane, the left power controller of described system is monitored by numeral and analog interface and is controlled left alternating-current distribution panel, left direct current panel and emergency switchboard; Right power controller is monitored by numeral and analog interface and is controlled right alternating-current distribution panel, right direct current panel and emergency switchboard; The state that left and right power controller is run to host computer feedback system by 1553B communication data bus and CAN communication data bus; Between the power controller of left and right by ARINC429 bus mutual separately control the information of switchboard; Engine controller, remote power controller by the power controller transmission to the left and right of RS485 bus and CAN separately control the running status of parts.Present invention achieves health diagnosis function, improve reliability and real-time, electric power system achieves uninterrupted power supply, fault tolerant electrical power supply and load torque obsever.
Description
Technical field
The invention belongs to automatic control technology field, especially relate to distributive redundancy type automatic power distribution control system for airplane.
Background technology
The aircraft distribution network that Aircraft Automatic Electrical Power System is formed primarily of each bus-bar, terminal and the distribution control module that is made up of respective processor, controller form.Primary power distribution is the part from generator to power supply bus-bar, and its control module is power controller PCU(Power Control Unit); Secondary power distribution is the part from 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).
Current aircraft automatic distribution control mode is mainly centralized, distributed and integrated distribution formula.Centralized automatic power distribution control system only has a central processing unit, if central processing unit breaks down, whole aircraft power system cannot normally be run, and therefore the reliability and stability of system are poor; There is no unified central processing unit in distributed automatic power distribution control system, cannot regulate and control aircraft power system system level, can produce between each long-range power supply unit and be difficult to the unified problem coordinated; When integrated distribution formula control system carries out centralized control to complicated aircraft electrical network, because the huge of system and control algolithm complexity can cause real-time to reduce.In the control mode that order is general, to the control of emergent distribution center, be difficult to the guaranteed reliability accomplishing higher level.
Primary power distribution control module PCU is the core of Aircraft Automatic Electrical Power System, and it seriously governs the power supply reliability of flight sequencing to the control reliability of aircraft distribution network.And the automatic distribution control mode of redundant distributions formula, all there is vital role to the reliability that the real-time and emergent distribution section that improve Systematical control 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, proposes distributive redundancy type automatic power distribution control system for airplane.Described system can carry out distributed controll to main ac/dc distribution section, carries out Redundant Control, improve the power supply reliability of aircraft primary distribution network to emergent distribution section.
For solving the problems of the technologies described above, the technical solution adopted in the present invention is:
Distributive redundancy type automatic power distribution control system for airplane, it is characterized in that, described system comprises the host computer connected by bus system, left power controller, right power controller, left alternating-current distribution panel, right alternating-current distribution panel, left direct current panel, right direct current panel, emergency switchboard, engine controller and remote power controller; Described left power controller monitors the running status of left alternating-current distribution panel, left direct current panel and emergency switchboard respectively by numeral and analog interface, and is controlled left alternating-current distribution panel, left direct current panel and emergency switchboard respectively by network reconfiguration logical operation and overcurrent protection computing; Described right power controller monitors the running status of right alternating-current distribution panel, right direct current panel and emergency switchboard respectively by numeral and analog interface, and is controlled right alternating-current distribution panel, right direct current panel and emergency switchboard respectively by network reconfiguration logical operation and overcurrent protection computing; Described host computer controls the state of left power controller, right power controller respectively, and shows the status information of left power controller, right power controller respectively;
Described left power controller, right power controller carry out Redundant Control to emergency switchboard jointly, and its method is as follows:
Determine the priority of left power controller and right power controller respectively; 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 controls unsuccessfully to emergency switchboard, then take over right power controller by left power controller to control emergency switchboard, 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 controls unsuccessfully to emergency switchboard, then take over left power controller by right power controller to control emergency switchboard, left power controller loses the control to emergency switchboard simultaneously.
Described bus system comprises avionics system bus and electrical system bus; Avionics system bus comprises 1553B communication data bus and CAN communication data bus, and electrical system bus comprises ARINC429 bus and RS485 communication data bus, CAN communication data bus; Host computer is connected with left power controller, right power controller respectively by avionics system bus; Between left power controller and right power controller by ARINC429 bus mutual separately control the running status of switchboard and self-monitoring result, and realized the synchronous operation of left power controller and right power controller by ARINC429 bus; Engine controller and remote power controller by RS485 communication data bus and CAN communication data bus respectively left power controller, right power controller feedback separately control the running status of parts.
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, described central processing unit and control circuit process the information that communication interface circuit, digital interface circuit and analog interface circuit receive and control the output of communication interface circuit, digital interface circuit and analog interface circuit respectively 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 aircraft distribution network; After filtering and power module conversion, power module exports 4 road voltage sources, is respectively 5V digital power, ± 15V analog power and 28V DC power power-supply.
Described central processing unit and control circuit complete status information process to aircraft primary distribution network, communication information process, control algolithm computing, control signal export and Autonomous test to self.
Described memory module static timing can store running status in the aircraft primary distribution network schedule time, the current operating conditions of real-time storage aircraft primary distribution network.
Described communication interface circuit comprises the RS485 communication interface of two remaining 1553B communication interface, two remaining ARINC429 communication bus interface, dual-redundancy CAN communication interface and band remaining interface.
Described digital interface circuit realizes power controller to the process of aircraft distribution network digital state signal and the driving to contactor on aircraft switchboard.
Described analog interface circuit realizes the process of power controller to aircraft distribution network simulating signal, simulating signal is converted to 0V to 3V voltage and sends into central processing unit.
The invention has the beneficial effects as follows: the present invention proposes distributive redundancy type automatic power distribution control system for airplane, the left power controller of described system is monitored by numeral and analog interface and is controlled left alternating-current distribution panel, left direct current panel and emergency switchboard; Right power controller is monitored by numeral and analog interface and is controlled right alternating-current distribution panel, right direct current panel and emergency switchboard; The state that left and right power controller is run to host computer feedback system by 1553B communication data bus and CAN communication data bus; Between the power controller of left and right by ARINC429 bus mutual separately control the information of switchboard; Engine controller, remote power controller by the power controller transmission to the left and right of RS485 bus and CAN separately control the running status of parts.Present invention achieves health diagnosis function, improve reliability and real-time, electric power system achieves uninterrupted power supply, fault tolerant electrical power supply and load torque obsever.
Accompanying drawing explanation
Fig. 1 is present system structural representation.
Fig. 2 is present system communication network schematic diagram.
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 the subroutine software flow schematic diagram that power controller of the present invention realizes to main AC/DC switchboard distributed controll.
Embodiment
Below in conjunction with accompanying drawing, the distributive redundancy type automatic power distribution control system for airplane that the present invention proposes is described in detail:
As shown in Figure 1, be distributive redundancy type automatic power distribution control system for airplane of the present invention, system comprises a host computer, two, left and right power controller, 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 monitor and forecast, and right alternating-current distribution panel and right direct current panel are by right power controller monitor and forecast, and emergency switchboard then left and right power controller all can monitor and forecast; The interface of power controller and switchboard comprises digital interface and analog interface.Left and right two power controllers communicate with host computer with by 1553B bus and CAN, between two power controllers, and power controller is communicated by ARINC429, CAN and RS485 bus with between engine controller, remote power controller.
As shown in Figure 2, the communication network of distributive redundancy type automatic power distribution control system for airplane is as follows: left and right two power controllers all have with upper strata avionics system bus and lower floor's electrical system bus and are connected, for upper strata avionics system bus, communicate with host computer mainly through 1553B bus and CAN, for lower floor's electrical system bus, mainly between two power controllers, and power controller is communicated by ARINC429, CAN and RS485 with between engine controller, remote power controller.The avionics system bus that power controller and host computer host computer adopt single channel CAN and 1553B bus to communicate with host computer as power controller; Two power controllers communicate with the compound remaining adopting single channel CAN and single channel RS485 bus to form between engine controller and remote power controller; Double channel A RINC429 is adopted to communicate between 2 power controllers.
As shown in Figure 3, left and right power controller takes 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 (as contactor state, Bus Voltage and frequency etc.), and it is inner by certain control algolithm computing at processor, the control signal of the online associated contact device of output distribution, control signal is after driving circuit amplifies, control each contactor, thus the automatic distribution realizing aircraft power distribution network controls and fault isolation; 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 with RPDU, and completion status monitoring is with feedback and receive the functions such as instruction; For aircraft electric network fault reason can be found out by PCU after electric network fault power-off, also need with ROM (read-only memory) on PCU, store the working condition of aircraft electrical network within a period of time.
Described power module completes the supply to power controller electric energy.Power module input has 2 tunnels, is respectively direct current bus-bar 28V power supply and accumulator 28V power supply in aircraft distribution network.This power supply, after filtering and power module conversion, obtains 4 road power supply voltage signals, is respectively 5V digital power, ± 15V analog power and 28VDC power power-supply.
Described central processing unit and control circuit are the cores of power controller, complete the status information process to aircraft primary distribution network, communication information process, control algolithm computing, control signal output and the Autonomous test to self.Wherein central processing unit is the dsp chip TMS320F2812 of TI company, includes the relative program that whole control system is run; Control circuit mainly comprises CPLD(EPM7128S) and peripheral circuit, realize address coding/decoding and correlation timing circuit mainly through Digital Logic.
Described memory module static timing can store aircraft primary distribution network running status within an hour, and dynamic realtime stores the current operating conditions of aircraft primary distribution network, and its core is Flash chip WF1M32B-G2UI3A.
Described communication interface circuit realizes the external communication interface of power controller, comprises the RS485 communication interface of two remaining 1553B communication interface, two remaining ARINC429 communication bus interface, dual-redundancy CAN communication interface and band remaining interface.
Described digital interface circuit realizes power controller to the hardware handles of aircraft distribution network digital state signal and the driving to contactor on aircraft switchboard.
Described analog interface circuit realizes power controller and nurses one's health the hardware of aircraft distribution network simulating signal, simulating signal is converted to 0 ~ 3V voltage and sends into central processing unit.
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, first initialization and initial Autonomous test is started, self-monitoring result will be uploaded to host computer, if Autonomous test normally, continues to run, otherwise just select continue or restart reset according to the instruction of host computer; System enters normal operating phase afterwards, carries out information acquisition, data processing, algorithm control algorithm, overcurrent protection computing, exports and controls result and carry out message exchange and storage; Also needing the process of carrying out On-line self-diagnosis survey in system normal course of operation, for judging that whether control output signal lost efficacy, if On-line self-diagnosis is surveyed find fault, reported to the police to host computer immediately, and selecting to continue or reset according to the instruction of host computer.
In described main program flow, obtain the reception that electrical network current operating conditions comprises the collection of digital signal, the collection of simulating signal and each bar communication bus data.
In described main program flow, computing reconfiguration of electric networks steering logic process is the core in software flow, and two, left and right power controller correspond to respective reconfiguration of electric networks algorithm.
As shown in Figure 5, the flow process that left and right power controller carries out distributed controll to left ac/dc switchboard and right ac/dc switchboard is separately as follows: when carrying out distributed controll, first correlated digital/the analog information on aircraft switchboard is read, and carry out data processing, then carry out network reconfiguration computing, draw the theoretic network reconfiguration result of calculation of aircraft distribution network
net, when
netrepresent when=1 and make corresponding branch road connect; When
netrepresent when=0 and make corresponding branch road disconnect; Determine whether to exist branch road overcurrent on switchboard simultaneously, then start calculating current guard time, if overcurrent more than time remaining 2s, then carry out overcurrent protection, the overcurrent protection instruction that order is corresponding
err=0, represent and disconnect overcurrent branch road.According to
netand
erron/off instruction final on synthesis switchboard
cmd.
The Redundant Control flow process of left and right power controller to emergent distribution section is as follows: when powering on initial, and first RPCU controls emergent distribution section; After system is normal, by Autonomous test, RPCU can judge whether relevant control instruction can realize, and LPCU is in supervision and Status of Backups simultaneously; Once the RPCU be possessed of control power is correlated with, Autonomous test does not pass through, then immediately control is licensed to LCPU, simultaneously self power out of hand; Be in after monitoring that the LPCU of status receives control, should control emergent distribution section immediately, prevent fault.
Claims (9)
1. distributive redundancy type automatic power distribution control system for airplane, it is characterized in that, described system comprises the host computer connected by bus system, left power controller, right power controller, left alternating-current distribution panel, right alternating-current distribution panel, left direct current panel, right direct current panel, emergency switchboard, engine controller and remote power controller; Described bus system comprises avionics system bus and electrical system bus; Described host computer is connected with left power controller, right power controller respectively by avionics system bus; Described left power controller is connected by electrical system bus with right power controller; Described engine controller is connected with left power controller, right power controller by electrical system bus respectively with remote power controller; Described left power controller is connected with left alternating-current distribution panel, left direct current panel and emergency switchboard respectively by numeral and analog interface, and monitor the running status of left alternating-current distribution panel, left direct current panel and emergency switchboard, respectively left alternating-current distribution panel, left direct current panel and emergency switchboard are controlled by network reconfiguration logical operation and overcurrent protection computing; Described right power controller is connected with right alternating-current distribution panel, right direct current panel and emergency switchboard respectively by numeral and analog interface, and monitor the running status of right alternating-current distribution panel, right direct current panel and emergency switchboard, respectively right alternating-current distribution panel, right direct current panel and emergency switchboard are controlled by network reconfiguration logical operation and overcurrent protection computing; Described host computer controls the state of left power controller, right power controller respectively, and shows the status information of left power controller, right power controller respectively;
Described left power controller, right power controller carry out Redundant Control to emergency switchboard jointly, and its method is as follows:
Determine the priority of left power controller and right power controller respectively; 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 controls unsuccessfully to emergency switchboard, then take over right power controller by left power controller to control emergency switchboard, 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 controls unsuccessfully to emergency switchboard, then take over left power controller by right power controller to control emergency switchboard, left power controller loses the control to emergency switchboard simultaneously.
2. distributive redundancy type automatic power distribution control system for airplane according to claim 1, is characterized in that, described bus system comprises avionics system bus and electrical system bus; Avionics system bus comprises 1553B communication data bus and CAN communication data bus, and electrical system bus comprises ARINC429 bus and RS485 communication data bus, CAN communication data bus; Host computer is connected with left power controller, right power controller respectively by avionics system bus; Between left power controller and right power controller by ARINC429 bus mutual separately control the running status of switchboard and self-monitoring result, and realized the synchronous operation of left power controller and right power controller by ARINC429 bus; Engine controller and remote power controller by RS485 communication data bus and CAN communication data bus respectively left power controller, right power controller feedback separately control the running status of parts.
3. distributive redundancy type automatic power distribution control system for airplane 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, described central processing unit and control circuit process the information that communication interface circuit, digital interface circuit and analog interface circuit receive and control the output of communication interface circuit, digital interface circuit and analog interface circuit respectively respectively, and described memory module provides storage space and buffer memory for central processing unit and control circuit.
4. distributive redundancy type automatic power distribution control system for airplane 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 aircraft distribution network; After filtering and power module conversion, power module exports 4 road voltage sources, is respectively 5V digital power, ± 15V analog power and 28V DC power power-supply.
5. distributive redundancy type automatic power distribution control system for airplane according to claim 3, it is characterized in that, described central processing unit and control circuit complete status information process to aircraft primary distribution network, communication information process, control algolithm computing, control signal export and Autonomous test to self.
6. distributive redundancy type automatic power distribution control system for airplane according to claim 3, it is characterized in that, described memory module static timing can store running status in the aircraft primary distribution network schedule time, the current operating conditions of real-time storage aircraft primary distribution network.
7. distributive redundancy type automatic power distribution control system for airplane according to claim 3, it is characterized in that, described communication interface circuit comprises the RS485 communication interface of two remaining 1553B communication interface, two remaining ARINC429 communication bus interface, dual-redundancy CAN communication interface and band remaining interface.
8. distributive redundancy type automatic power distribution control system for airplane according to claim 3, is characterized in that, described digital interface circuit realizes power controller to the process of aircraft distribution network digital state signal and the driving to contactor on aircraft switchboard.
9. distributive redundancy type automatic power distribution control system for airplane according to claim 3, it is characterized in that, described analog interface circuit realizes the process of power controller to aircraft distribution network simulating signal, simulating signal is converted to 0V to 3V voltage and sends into central processing unit.
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Families Citing this family (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 |
| CN105549424B (en) * | 2016-01-06 | 2019-04-23 | 南京航空航天大学 | A kind of jumbo jet busbar power control unit simulation system and method |
| CN105449842B (en) * | 2016-01-08 | 2017-09-15 | 清华大学 | A kind of automobile-used remaining power supply |
| 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 |
| US10998935B2 (en) * | 2019-02-20 | 2021-05-04 | Honeywell Limited | Secondary electric power distribution system (SEPDS) to facilitate aircraft connectivity |
| CN115693928B (en) * | 2022-10-14 | 2023-06-20 | 哈尔滨工业大学 | ZYNQ-based airplane direct-current remote power distribution unit and power distribution control method |
Citations (4)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2468652B (en) * | 2009-03-16 | 2011-08-31 | Ge Aviat Systems Ltd | Electrical power distribution |
-
2013
- 2013-05-31 CN CN201310216683.XA patent/CN103309319B/en not_active Expired - Fee Related
Patent Citations (4)
| 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 |
| 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 |
|---|
| Novel Aircraft Electrical Power Distribution System Based on Distributed Computer;Yang Shanshui et al;《Transactions of Nanjing University of Aeronautics & Astronautics》;20011231;第18卷(第2期);224-228 * |
| Redundancy Technology for Aircraft Multi-Channel DC Power Supply System;Yang Shanshui et al;《Transactions of Nanjing University of Aeronautics & Astronautics》;20071231;第24卷(第4期);305-309 * |
| 基于可靠性的航天器供配电系统技术研究;孔令杰 等;《江苏航空》;20121231(第4期);10-13 * |
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