CN204089325U - The novel power supply circuits of a kind of flight control system - Google Patents
The novel power supply circuits of a kind of flight control system Download PDFInfo
- Publication number
- CN204089325U CN204089325U CN201420464954.3U CN201420464954U CN204089325U CN 204089325 U CN204089325 U CN 204089325U CN 201420464954 U CN201420464954 U CN 201420464954U CN 204089325 U CN204089325 U CN 204089325U
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- relay
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- flight control
- power supply
- busbar
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 58
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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Abstract
The novel power supply circuits of a kind of flight control system, this circuit comprises No. 1 busbar, No. 2 busbars, flight control system, total power switch, contactor, batteries, relays etc.These power supply circuits be provided with two-way independently Power supply and a road batteries power, when two-way independent current source wherein a road power failure time powered to flight control system by another road power supply, achieve fly-by-wire flight control system triplex redundance and power.Because batteries is directly powered to flight control system by relay, when ground power supply and machine power source change and No. 1 busbar and No. 2 busbars change and the power failure caused time, flight control system still can continue to be powered from batteries, achieves the continuous uninterrupted power supply of fly-by-wire flight control system.Be provided with latching circuit owing to there being a road to power, be in powered operation state all the time, effectively can solve total power switch misoperation, inefficacy and other two-way power supply fault and cause the fail-all problem of flight control system triplex redundance power supply.
Description
Technical field
The utility model relates to airplane design technical field, particularly the novel power supply circuits of a kind of flight control system.
Background technology
Along with aircraft is to many electricity and complete electric future development, the flight control system of Flight By Wire instead of original mechanical handling control system, higher requirement is had with controlling to the system configuration of present generation aircraft electric power system, for guaranteeing that fly-by-wire flight control system is safe and reliable, continuous uninterrupted power supply must be provided to flight control system, and meet the failure tolerant requirement of redundant electrical pow er supply requirement and secondary failure work.
Summary of the invention
In order to solve the problem, the purpose of this utility model is to provide the novel power-supplying circuit of a kind of flight control system, and the redundant electrical pow er supply proposed electric power system to meet aircraft full digital fly-by-wire flight control system requires, continuous uninterrupted power supply requires and fault tolerant electrical power supply requirement.
The novel power supply circuits of this flight control system, comprise No. 1 busbar, No. 2 busbars, flight control system, total power switch, contactor, batteries, relay a, b, c, d, diode a, b, circuit breaker a, b and fuse, described No. 1 busbar is connected with right generator or ground power supply, described No. 2 busbars are connected with left generator or ground power supply, described right generator or ground power supply are powered to No. 1 busbar, described left generator or ground power supply are powered to No. 2 busbars, described diode a positive pole is connected with ground power supply, negative pole is connected with relay a control end positive pole, described diode b positive pole is connected with left generator, negative pole is connected with relay a control end positive pole, described batteries often to be made war with relay d by fuse and is connected, be connected with flight control system by relay d common port, described batteries is also connected with relay d control end positive pole by fuse, relay d control end negative pole is connected to ground by total power switch, after described total power switch is connected, described batteries passes through fuse, relay d provides a road to power to flight control system, it is characterized in that: described No. 1 busbar is connected with No. 2 busbars by contactor, two control end one end of described contactor are connected to ground, the other end is connected with left and right generator failure signal, described No. 1 busbar often to be made war with relay c by circuit breaker b and is connected, be connected with flight control system by relay c common port, described No. 2 busbars often to be made war with relay a by circuit breaker a and are connected, be connected with flight control system by relay a common port, described relay a, b, the control end negative pole of c is connected to ground by total power switch, described No. 1 busbar is also connected with relay b control end positive pole and relay c control end positive pole by circuit breaker b, described relay b is also connected with normal battle of relay b with the control end negative pole of relay c, the common port of described relay b is connected to ground.When described No. 1 busbar and No. 2 busbars are powered simultaneously, described contactor does not work, described No. 1 busbar is not communicated with No. 2 busbars, after described total power switch is connected, described relay a, c work, described No. 1 busbar provides a road to power by circuit breaker b, relay c to flight control system, and described No. 2 busbars provide a road to power by circuit breaker a, relay a to flight control system.Described No. 1 busbar and No. 2 busbars wherein any one power supply time, described contactor work, described No. 1 busbar is communicated with grid-connected powered operation with No. 2 busbars, after described total power switch is connected, described relay a, c work, described No. 1 busbar provides a road to power by circuit breaker b, relay c to flight control system, and No. 2 busbars provide a road to power by circuit breaker a, relay a to flight control system simultaneously.Described No. 1 busbar is when powered operation, after total power switch is connected, the while that described relay c working, relay b also works, be connected because described relay c and the control end negative pole of relay b are made war with the normal of relay b, the common port of relay b is connected to ground, the control end negative pole of described relay c is by the self-locking of relay b ground connection, described relay c works all the time, when total power switch misoperation, inefficacy, cable get loose and other two-way power supply fault time, described No. 1 busbar is powered to flight control system by circuit breaker b, relay c all the time.
The novel power supply circuits of this flight control system be provided with two-way independently Power supply and a road batteries power, when two-way independent current source wherein a road power failure time powered to flight control system by another road power supply, achieve fly-by-wire flight control system triplex redundance and power.Because batteries is directly powered to flight control system by relay, when ground power supply and machine power source change and No. 1 busbar and No. 2 busbars change and the power failure caused time, flight control system still can continue to be powered from batteries, achieves the continuous uninterrupted power supply of fly-by-wire flight control system.Latching circuit is provided with owing to there being a road to power, all the time be in powered operation state, effectively can solve total power switch misoperation, inefficacy, cable gets loose and two-way power supply circuit common mode/Single Point of Faliure causes the fail-all problem of flight control system triplex redundance power supply in addition.
Accompanying drawing explanation
Fig. 1 is the utility model power supply the principle figure.
In figure: 1-1 busbar, 2-2 busbar, 3-flight control system, 4-total power switch, 5-contactor, 6-batteries, 7-relay a, 8-relay b, 9-relay c, 10-relay d, 11-diode a, 12-diode b, 13-circuit breaker a, 14-circuit breaker b, 15-fuse.
Embodiment
Below in conjunction with the drawings and the specific embodiments, the utility model is described in further detail.
As shown in Figure 1, the novel power supply circuits of this flight control system, comprise No. 1 busbar 1, No. 2 busbars 2, flight control system 3, total power switch 4, contactor 5, batteries 6, relay a7, relay b8, relay c9, relay d10, diode a11, diode b12, circuit breaker a13, circuit breaker b14 and fuse 15.The novel power supply circuits of this flight control system are the types adopting low-voltage DC supply system for main power source, more than during concrete enforcement, each device should carry out design and selection according to the model of concrete aircraft, size, capacity, is placed in aircraft relevant position and connects shown in accompanying drawing 1.No. 1 busbar 1 is connected with right generator or ground power supply (aircraft is when ground), and No. 2 busbars 2 are connected with left generator or ground power supply (aircraft is when ground), and aircraft electrical power supply system design and installation specification is pressed in specific requirement.Right generator or ground power supply provide 28 volts of DC power supply to No. 1 busbar 1, and left generator or ground power supply provide 28 volts of DC power supply to No. 2 busbars 2, and batteries 6 provides 24 volts of DC power supply.Because total power switch 4 is connected on control circuit relay earth loop, after total power switch 4 is connected:
1. left generator or ground power supply (aircraft is when ground) provide the direct current supply of 28 volts, a road by No. 2 busbars 2, circuit breaker a13, relay a7 to flight control system 3.
2. right generator or ground power supply (aircraft is when ground) provide the direct current supply of 28 volts, a road by No. 1 busbar 1, circuit breaker b14, relay c9 to flight control system 3.
3. batteries 6 provides the direct current supply of 24 volts, a road by fuse 15, relay d10 to flight control system 3, because power supply is all grid-connected powered operation, when flight control system 3 is at 28 volts of voltage battery-powered operation, because batteries 6 voltage is low, be in charged state, when in flight control system 3,28 volts of power voltage supplies one lose, batteries 6 is uninterrupted at once provides 24 volts of direct current supplys of meeting an urgent need to flight control system 3.
During No. 4.1 busbar 1 powered operation, the while that relay c9 working, relay b8 also works, the control end negative pole of relay c9 is by the self-locking of relay b8 ground connection, relay c9 works all the time, when total power switch 4 misoperation, inefficacy, cable get loose and other two-way power supply fault time, No. 1 busbar 1 provides an appearance of a street wrong 28 volts of direct current supplys by circuit breaker b14, relay c9 to flight control system 3 all the time.
5. the switching of No. 1 busbar 1 and No. 2 busbar 2 grid-connected powered operations when contactor 5 mainly controls No. 1 busbar 1 and No. 2 independently-powered operations of busbar 2 and arbitrary generator failure when left and right generator works simultaneously.
Claims (4)
1. the novel power supply circuits of flight control system, comprise No. 1 busbar [1], No. 2 busbars [2], flight control system [3], total power switch [4], contactor [5], batteries [6], relay a [7], b [8], c [9], d [10], diode a [11], b [12], circuit breaker a [13], b [14] and fuse [15], described No. 1 busbar [1] is connected with right generator or ground power supply, described No. 2 busbars [2] are connected with left generator or ground power supply, described right generator or ground power supply are powered to No. 1 busbar [1], described left generator or ground power supply are powered to No. 2 busbars [2], described diode a [11] positive pole is connected with ground power supply, negative pole is connected with relay a [7] control end positive pole, described diode b [12] positive pole is connected with left generator, negative pole is connected with relay a [7] control end positive pole, described batteries [6] often to be made war with relay d [10] by fuse [15] and is connected, be connected with flight control system [3] by relay d [10] common port, described batteries [6] is also connected with relay d [10] control end positive pole by fuse [15], relay d [10] control end negative pole is connected to ground by total power switch [4], after described total power switch [4] is connected, described batteries [6] is by fuse [15], relay d [10] provides a road to power to flight control system [3], it is characterized in that: described No. 1 busbar [1] is connected with No. 2 busbars [2] by contactor [5], two control end one end of described contactor [5] are connected to ground, the other end is connected with left and right generator failure signal, described No. 1 busbar [1] often to be made war with relay c [9] by circuit breaker b [14] and is connected, be connected with flight control system [3] by relay c [9] common port, described No. 2 busbars [2] often to be made war with relay a [7] by circuit breaker a [13] and are connected, be connected with flight control system [3] by relay a [7] common port, described relay a [7], b [8], the control end negative pole of c [9] is connected to ground by total power switch [4], described No. 1 busbar [1] is also connected with relay b [8] control end positive pole and relay c [9] control end positive pole by circuit breaker b [14], described relay b [8] is also connected with normal battle of relay b [8] with the control end negative pole of relay c [9], the common port of described relay b [8] is connected to ground.
2. the novel power supply circuits of flight control system described in a Ju claim 1, it is characterized in that: when described No. 1 busbar [1] and No. 2 busbars [2] are powered simultaneously, described contactor [5] does not work, described No. 1 busbar [1] is not communicated with No. 2 busbars [2], after described total power switch [4] is connected, described relay a [7], c [9] works, described No. 1 busbar [1] is by circuit breaker b [14], relay c [9] provides a road to power to flight control system [3], described No. 2 busbars [2] are by circuit breaker a [13], relay a [7] provides a road to power to flight control system [3].
3. the novel power supply circuits of flight control system described in a Ju claim 1, it is characterized in that: described No. 1 busbar [1] and No. 2 busbars [2] wherein any one power supply time, described contactor [5] works, described No. 1 busbar [1] is communicated with grid-connected powered operation with No. 2 busbars [2], after described total power switch [4] is connected, described relay a [7], c [9] works, described No. 1 busbar [1] is by circuit breaker b [14], relay c [9] provides a road to power to flight control system [3], No. 2 busbars [2] are by circuit breaker a [13] simultaneously, relay a [7] provides a road to power to flight control system [3].
4. the novel power supply circuits of flight control system described in a Ju claim 1, it is characterized in that: described No. 1 busbar [1] is when powered operation, after total power switch [4] is connected, described relay c [9] work simultaneously relay b [8] also works, because described relay c [9] is connected with normal battle of relay b [8] with the control end negative pole of relay b [8], the common port of relay b [8] is connected to ground, the control end negative pole of described relay c [9] is by relay b [8] ground connection self-locking, described relay c [9] works all the time, when total power switch [4] misoperation, lost efficacy, cable get loose and other two-way power supply fault time, described No. 1 busbar [1] is all the time by circuit breaker b [14], relay c [9] powers to flight control system [3].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201420464954.3U CN204089325U (en) | 2014-08-18 | 2014-08-18 | The novel power supply circuits of a kind of flight control system |
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| CN201420464954.3U CN204089325U (en) | 2014-08-18 | 2014-08-18 | The novel power supply circuits of a kind of flight control system |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104600832A (en) * | 2015-01-26 | 2015-05-06 | 哈尔滨飞机工业集团有限责任公司 | High power load loading equipment emergency power supply control system and control method thereof |
| CN105024452A (en) * | 2015-08-11 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | DC uninterrupted power supply method and line |
| CN105391162A (en) * | 2015-11-25 | 2016-03-09 | 北京象限空间科技有限公司 | Uninterrupted power supply system for unmanned aerial vehicle |
| CN105738657A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Aircraft measurement and control system automatic power supply device |
| CN106451689A (en) * | 2016-12-15 | 2017-02-22 | 南通华夏飞机工程技术股份有限公司 | Supply circuit of direct current power vehicle |
| CN107910948A (en) * | 2017-12-01 | 2018-04-13 | 中国直升机设计研究所 | It is a kind of to be used to reduce device and Helicopter Electrical Power system that helicopter turns the electric time |
| CN107919725A (en) * | 2017-11-16 | 2018-04-17 | 陕西航空电气有限责任公司 | A kind of airplane power source control box using Interleaved control configuration |
| CN108011443A (en) * | 2017-12-01 | 2018-05-08 | 中国直升机设计研究所 | A kind of helicopter is non-emergency to load uninstalling system and its discharging method |
| CN108288853A (en) * | 2018-04-04 | 2018-07-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft DC power supply system and method for supplying power to |
| CN109120057A (en) * | 2017-06-22 | 2019-01-01 | 中航贵州飞机有限责任公司 | A kind of aircraft energizer uninterruptedly switches power supply unit |
| CN110667866A (en) * | 2018-07-03 | 2020-01-10 | 上海航空电器有限公司 | External power supply voltage, overload, frequency and open-phase protection structure of bus bar power controller |
| CN111756284A (en) * | 2020-06-17 | 2020-10-09 | 江西洪都航空工业集团有限责任公司 | Dual-channel aircraft generator control device with dual-redundancy design |
| CN112072778A (en) * | 2020-08-28 | 2020-12-11 | 中电科芜湖通用航空产业技术研究院有限公司 | Power distribution management system and method for double-engine aircraft |
| CN112895974A (en) * | 2021-01-19 | 2021-06-04 | 四川腾盾科技有限公司 | Method for increasing the reliability of an onboard battery system and corresponding operating method |
| CN113054639A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Power supply control circuit of flight control system |
| CN113120246A (en) * | 2021-04-28 | 2021-07-16 | 九成通用飞机设计制造(大连)有限公司 | Implementation method for controlling and protecting power supply system of double-engine airplane |
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2014
- 2014-08-18 CN CN201420464954.3U patent/CN204089325U/en not_active Expired - Lifetime
Cited By (27)
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| CN104600832A (en) * | 2015-01-26 | 2015-05-06 | 哈尔滨飞机工业集团有限责任公司 | High power load loading equipment emergency power supply control system and control method thereof |
| CN105024452B (en) * | 2015-08-11 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | DC uninterrupted power supply method and line |
| CN105024452A (en) * | 2015-08-11 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | DC uninterrupted power supply method and line |
| CN105391162A (en) * | 2015-11-25 | 2016-03-09 | 北京象限空间科技有限公司 | Uninterrupted power supply system for unmanned aerial vehicle |
| CN105738657A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Aircraft measurement and control system automatic power supply device |
| CN106451689A (en) * | 2016-12-15 | 2017-02-22 | 南通华夏飞机工程技术股份有限公司 | Supply circuit of direct current power vehicle |
| CN106451689B (en) * | 2016-12-15 | 2018-07-27 | 南通华夏飞机工程技术股份有限公司 | A kind of power supply circuit of DC power supply vehicle |
| CN109120057A (en) * | 2017-06-22 | 2019-01-01 | 中航贵州飞机有限责任公司 | A kind of aircraft energizer uninterruptedly switches power supply unit |
| CN109120057B (en) * | 2017-06-22 | 2023-05-23 | 中航贵州飞机有限责任公司 | Uninterrupted switching power supply device for aircraft ground power supply |
| CN107919725A (en) * | 2017-11-16 | 2018-04-17 | 陕西航空电气有限责任公司 | A kind of airplane power source control box using Interleaved control configuration |
| CN107919725B (en) * | 2017-11-16 | 2021-01-05 | 陕西航空电气有限责任公司 | Aviation power supply control box adopting staggered control configuration |
| CN107910948A (en) * | 2017-12-01 | 2018-04-13 | 中国直升机设计研究所 | It is a kind of to be used to reduce device and Helicopter Electrical Power system that helicopter turns the electric time |
| CN108011443A (en) * | 2017-12-01 | 2018-05-08 | 中国直升机设计研究所 | A kind of helicopter is non-emergency to load uninstalling system and its discharging method |
| CN107910948B (en) * | 2017-12-01 | 2021-05-07 | 中国直升机设计研究所 | Device for reducing helicopter power conversion time and helicopter power system |
| CN108011443B (en) * | 2017-12-01 | 2021-02-26 | 中国直升机设计研究所 | Non-emergency load unloading system and unloading method for helicopter |
| CN108288853A (en) * | 2018-04-04 | 2018-07-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft DC power supply system and method for supplying power to |
| CN108288853B (en) * | 2018-04-04 | 2024-05-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Direct current power supply system and power supply method for airplane |
| CN110667866A (en) * | 2018-07-03 | 2020-01-10 | 上海航空电器有限公司 | External power supply voltage, overload, frequency and open-phase protection structure of bus bar power controller |
| CN113054639A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Power supply control circuit of flight control system |
| CN111756284A (en) * | 2020-06-17 | 2020-10-09 | 江西洪都航空工业集团有限责任公司 | Dual-channel aircraft generator control device with dual-redundancy design |
| CN112072778A (en) * | 2020-08-28 | 2020-12-11 | 中电科芜湖通用航空产业技术研究院有限公司 | Power distribution management system and method for double-engine aircraft |
| CN112072778B (en) * | 2020-08-28 | 2024-09-10 | 中电科芜湖通用航空产业技术研究院有限公司 | Power distribution management system and method for double-engine aircraft |
| CN112895974A (en) * | 2021-01-19 | 2021-06-04 | 四川腾盾科技有限公司 | Method for increasing the reliability of an onboard battery system and corresponding operating method |
| CN113120246A (en) * | 2021-04-28 | 2021-07-16 | 九成通用飞机设计制造(大连)有限公司 | Implementation method for controlling and protecting power supply system of double-engine airplane |
| CN113120246B (en) * | 2021-04-28 | 2023-12-12 | 九成通用飞机设计制造(大连)有限公司 | Implementation method for controlling and protecting power supply system of double-engine aircraft |
| CN115432190A (en) * | 2022-09-22 | 2022-12-06 | 中国商用飞机有限责任公司 | Electric aircraft comprehensive electric propulsion system |
| WO2024060567A1 (en) * | 2022-09-22 | 2024-03-28 | 中国商用飞机有限责任公司 | Integrated electric propulsion system for electric aircrafts |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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| CX01 | Expiry of patent term |
Granted publication date: 20150107 |