CN103587707B - A kind of Electronic Flight Instrument electric power system - Google Patents
A kind of Electronic Flight Instrument electric power system Download PDFInfo
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- CN103587707B CN103587707B CN201310577406.1A CN201310577406A CN103587707B CN 103587707 B CN103587707 B CN 103587707B CN 201310577406 A CN201310577406 A CN 201310577406A CN 103587707 B CN103587707 B CN 103587707B
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Abstract
The invention provides one and can solve blank screen phenomenon, do not increase again the Electronic Flight Instrument electric power system of the operation burden of aviator, this system comprises the electronic type attitude director indicator be arranged on aircraft DC breaker plate, electron type level notch indicator, display processor, emergent bus-bar, power transfer relay.By emergent bus-bar for electronic flight meter system provides stable power supply, automatically provide EFIS to show required power supply, eliminate puzzlement display power supply switching manipulation being brought to aviator.
Description
Technical field
The invention belongs to airplane synthetic avionics technical field, particularly a kind of Electronic Flight Instrument electric power system.
Background technology
Electronic flight meter system (EFIS) provides the display of the information such as flying quality and navigation data for left and right driving, it receives the output signal from receiving heading and attitude system, air data system, autopilot, omnidirectional range/instrument landing/marker beacon system, macrometer, automatic direction finder, navigationsystem, radio altimeter and weather radar system on aircraft, for left and right driving provides corresponding display information.And for showing meteorological radar, guidance station/way point, flight-control mode, comparing warning, Airspeed Tendency, checklist and diagnostic message.There is provided Pre-select Heading and main channel etc. for information about to autopilot simultaneously.
Circuit breaker by being arranged on EADI, EHSI, DPU, DCP major alarm on electronic type attitude director indicator (EADI) on left DC circuit breaker plate, electron type level notch indicator (EHSI), display processor (DPU), display control board (DCP) major alarm and right DC circuit breaker plate on aircraft is powered to the armamentarium of EFIS system.The equipment of directly being powered by circuit breaker has left and right EADI; Left and right EHSI and EFD fan; Left and right DPU and DPU fan; Left and right DCP; Left and right II class approach light; Left and right major alarm lamp/reset button.After starting energising, equipment and fan thereof work simultaneously, to prevent equipment excess temperature and reduction of service life.By serial digital bus between two DPU, this side joint is received from aircraft with the information transmission of side apparatus to opposite side, driver output for subsequent use is also sent to the driving input channel for subsequent use of opposite side DPU simultaneously.This kind of power supply mode is comparatively simple, but Problems existing clearly, when ground and machine power source conversion (engine starting), Electronic Flight Instrument telltale can be caused to occur moment blank screen phenomenon; And under aircraft is in emergency service state, EFIS quits work, and will cause the loss of crucial navigation information.
There is above problem and mainly come from the airplane design initial stage in the design of former electric power system, considers the loading level of storage battery, is the flying power of storage battery 30min under guarantee emergency rating, EFIS is directly connected to normal bus-bar.Be increase Electronic Flight Instrument display power supply switch for head it off proposes a scheme, after engine starting is stable, connect Electronic Flight Instrument display power supply switch.But this kind of power supply plan adds extra operation burden to aviator, and when this display power supply switch failure, flying instruments will thoroughly quit work, and does not consider margin of safety problem.
By constantly test and improvement, design Bus Voltage when one can solve engine starting to reduce instantaneously, Electronic Flight Instrument telltale moment blank screen phenomenon, does not increase again the operation burden of aviator, does not cut down a kind of Electronic Flight Instrument electric power system of any function of flight instrument system.This system eventually through seaworthiness application, and solves former electric power system Problems existing and shortcoming by ground experiment checking.
Summary of the invention
The object of the present invention is to provide one to solve blank screen phenomenon, do not increase again the Electronic Flight Instrument electric power system of the operation burden of aviator.
A kind of Electronic Flight Instrument electric power system, this system comprises the left electronic type attitude director indicator (EADI) be arranged on aircraft left DC circuit breaker plate, left electron type level notch indicator (EHSI), left display processor (DPU), left emergent bus-bar and the right electronic type attitude director indicator (EADI) be arranged on aircraft right DC circuit breaker plate, right electron type level notch indicator (EHSI), right display processor (DPU), power transfer relay, right emergent bus-bar, mounting bracket, the upper left electronic type attitude director indicator (EADI) of left DC circuit breaker, left electron type level notch indicator (EHSI), the power supply of left display processor (DPU) is connected directly to left emergent bus-bar, the power supply of the right electronic type attitude director indicator (EADI) on right DC circuit breaker, right electron type level notch indicator (EHSI), right display processor (DPU) is connected to right emergent bus-bar by power transfer relay, power transfer relay is composed in parallel by the relay that two were done Anti-misplug design, and the excitatory end of power transfer relay is connected with the normal bus-bar of major alarm reset circuit breaker in flight instrument system, power transfer relay is connected to avionics system electronic equipment rack by mounting bracket.
Problem that beneficial effect of the present invention is that actv. solves by emergent bus-bar for electronic flight meter system provides stable power supply " blank screen "; Improve the margin of safety of the crucial navigation information display of driving compartment, namely under emergency service state, flight instrument system will have a set of display system continuous firing, ensure that critical fligh data can not be lost.Switching relay made by two the relay that Anti-misplug designs and composed in parallel, and accomplished that redundancy is arranged, and when wherein any one relay failure, another can continuous firing, can not cause right side flying quality disappearance; By excitatory for the relay normal bus-bar being connected to major alarm reset circuit breaker in flight instrument system; Do not affect the conversion operations of display control board on the one hand, do not increase extra circuit breaker on the other hand.Relay is connected to electronic equipment rack by mounting bracket.Be easy to the change of supply line, be easy to ground maintenance simultaneously.
Native system shows required power supply owing to automatically providing EFIS, thus eliminates puzzlement display power supply switching manipulation being brought to aviator, and alleviate the operation bidirectional burden of aviator, actv. solves the problem that user proposes.Below in conjunction with specific embodiment, this invention is described in further detail.
Accompanying drawing explanation
Fig. 1 primary electron flying instruments is powered left-sided system block diagram
Fig. 2 primary electron flying instruments is powered right-sided system block diagram
Electronic Flight Instrument after Fig. 3 optimization is powered left-sided system block diagram
Electronic Flight Instrument after Fig. 4 optimization is powered right-sided system block diagram
Specific embodiment
Can find out that two cover flying instrumentss are connected directly to normal DC electricity by Fig. 1, Fig. 2, and the generation of blank screen phenomenon will be caused when direct current (DC) is in electric current instantaneous variation.
And Fig. 3, Fig. 4 provide the Electronic Flight Instrument electric power system after a kind of optimization, and this kind of prioritization scheme has been verified at aircraft, and actv. solves the fault and defect that former electric power system brings.This Electronic Flight Instrument electric power system, comprises the left electronic type attitude director indicator (hereinafter referred to as EADI) be arranged on aircraft left DC circuit breaker plate, left electron type level notch indicator (hereinafter referred to as EHSI), left display processor (hereinafter referred to as DPU), left emergent bus-bar and is arranged on right EADI, the right EHSI on aircraft right DC circuit breaker plate, right DPU, power transfer relay, right emergent bus-bar, mounting bracket.The power supply of left EADI, left EHSI, left DPU is connected directly to a described left side and meets an urgent need bus-bar, for the display of navigation information crucial under emergency rating as shown in Figure 3.The power supply of the right EADI as shown in Figure 4 on right DC circuit breaker, right EHSI, right DPU is connected to the described right side by two power transfer relays in parallel and meets an urgent need bus-bar; The excitatory end of power transfer relay is connected to normal bus-bar.The effect of relay mainly contains: under aircraft is in emergency service situation, and a set of flying instruments in the right can not the electricity of battery consumption, ensure that enough emergent flying powers; Under supply regular power situation, when any one relay failure, right side flight instrument system can not quit work because of power down, eliminates the potential safety hazard that Single Point of Faliure brings to aircraft.
Claims (1)
1. an Electronic Flight Instrument electric power system, comprises the left electronic type attitude director indicator (EADI) be arranged on aircraft left DC circuit breaker plate, left electron type level notch indicator (EHSI), left display processor (DPU), left emergent bus-bar; Be arranged on the right electronic type attitude director indicator (EADI) on aircraft right DC circuit breaker plate, right electron type level notch indicator (EHSI), right display processor (DPU), power transfer relay, right emergent bus-bar, mounting bracket, it is characterized in that: the power supply of described left DC circuit breaker upper left electronic type attitude director indicator (EADI), left electron type level notch indicator (EHSI), left display processor (DPU) is connected directly to a described left side and meets an urgent need bus-bar; The power supply of the right electronic type attitude director indicator (EADI) on described right DC circuit breaker, right electron type level notch indicator (EHSI), right display processor (DPU) is connected to the described right side by described power transfer relay and meets an urgent need bus-bar; Described power transfer relay is composed in parallel by the relay that two were done Anti-misplug design, and the excitatory end of described power transfer relay is connected with the normal bus-bar of major alarm reset circuit breaker in flight instrument system; Described power transfer relay is connected to avionics system electronic equipment rack by mounting bracket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310577406.1A CN103587707B (en) | 2013-11-15 | 2013-11-15 | A kind of Electronic Flight Instrument electric power system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310577406.1A CN103587707B (en) | 2013-11-15 | 2013-11-15 | A kind of Electronic Flight Instrument electric power system |
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| Publication Number | Publication Date |
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| CN103587707A CN103587707A (en) | 2014-02-19 |
| CN103587707B true CN103587707B (en) | 2015-08-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310577406.1A Active CN103587707B (en) | 2013-11-15 | 2013-11-15 | A kind of Electronic Flight Instrument electric power system |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110979706B (en) * | 2019-10-11 | 2022-12-30 | 中国直升机设计研究所 | Dual-voltage helicopter power supply system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201066769Y (en) * | 2007-08-02 | 2008-05-28 | 西安威胜航空科技发展有限公司 | Plane power management system |
| CN102520621A (en) * | 2011-11-22 | 2012-06-27 | 中国商用飞机有限责任公司 | Analog control board of aircraft power supply system |
| WO2012112090A1 (en) * | 2011-02-17 | 2012-08-23 | Saab Ab | Flight data display |
| CN202915931U (en) * | 2012-08-20 | 2013-05-01 | 中航华东光电有限公司 | Display of airplane emergency electronic backup instrument |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2909233B1 (en) * | 2006-11-23 | 2011-03-04 | Hispano Suiza Sa | POWERING AN AIRCRAFT IN ELECTRICAL ENERGY |
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- 2013-11-15 CN CN201310577406.1A patent/CN103587707B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201066769Y (en) * | 2007-08-02 | 2008-05-28 | 西安威胜航空科技发展有限公司 | Plane power management system |
| WO2012112090A1 (en) * | 2011-02-17 | 2012-08-23 | Saab Ab | Flight data display |
| CN102520621A (en) * | 2011-11-22 | 2012-06-27 | 中国商用飞机有限责任公司 | Analog control board of aircraft power supply system |
| CN202915931U (en) * | 2012-08-20 | 2013-05-01 | 中航华东光电有限公司 | Display of airplane emergency electronic backup instrument |
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| CN103587707A (en) | 2014-02-19 |
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Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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Effective date of registration: 20210617 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |
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