CN104648660A - Airplane dual-redundancy digital type undercarriage retraction/extension controller - Google Patents
Airplane dual-redundancy digital type undercarriage retraction/extension controller Download PDFInfo
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- CN104648660A CN104648660A CN201310603629.0A CN201310603629A CN104648660A CN 104648660 A CN104648660 A CN 104648660A CN 201310603629 A CN201310603629 A CN 201310603629A CN 104648660 A CN104648660 A CN 104648660A
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Abstract
The invention belongs to the technical field of undercarriage control and particularly relates to an airplane dual-redundancy digital type undercarriage retraction/extension controller. The system comprises two working channels which are redundancies of each other; each working channel comprises a proximity sensor signal acquisition circuit, a handle signal acquisition circuit, a DSP minimum system and an output driving circuit; the two DSP minimum systems are connected by a crossed channel data chain; a switching circuit is connected with the two DSP minimum systems and the two output driving circuits respectively; and the output driving circuits are connected with one of the two DSP minimum systems and the switching circuit. The airplane dual-redundancy digital type undercarriage retraction/extension controller adopts electric dual-redundancy control and selects a DSP chip as a processor chip, so that an undercarriage retraction/extension system is simplified and has higher reliability; and the control rate is convenient to realize and adjust. The undercarriage retraction/extension controller adopts the dual-redundancy configuration so that the fault-tolerant capability of primary malfunction work and secondary malfunction safety can be realized.
Description
Technical field
The invention belongs to alighting gear control technology field, particularly relate to the two redundancy digital type undercarriage control controller of a kind of aircraft.
Background technology
Undercarriage packing controller is as important airborne equipment, and can undercarriage control controller normally work and will have a strong impact on aircraft safety.
The undercarriage control control system of fax logic control class, be provided with the computing machine of undercarriage control controller class, undercarriage control controller inside arranges dsp system, dsp system sends control command according to the signal of proximity transducer of folding and unfolding handle and monitoring alighting gear and hatch door position, drive the magnet coil of undercarriage control electromagnetic valve, thus realize folding and unfolding control and the sequence coordination of alighting gear and hatch door.But will realize " the two redundancy digital type undercarriage control controller of aircraft " does not have in disclosed data.
Summary of the invention
The object of the invention is: the two redundancy digital type undercarriage control controller of aircraft of the present invention receives the signal of proximity transducer and folding and unfolding handle, produces corresponding output command by given control algorithm, drives electromagnetic valve to complete the draw-in and draw-off function of undercarriage.Because undercarriage control controller adopts two redundant configurations, primary fault work, twice fail-safe fault-tolerant ability can be realized.
Technical scheme of the present invention is: the two redundancy digital type undercarriage control controller of a kind of aircraft, comprise the servicesubway of two remainings each other, each servicesubway comprises proximity transducer signal acquisition circuit, handle signal acquisition circuit, DSP minimum system and output driving circuit, two DSP minimum systems are connected by cross channel data link, commutation circuit is connected with two DSP minimum systems, two output driving circuits respectively, and output driving circuit is connected with one of two DSP minimum systems and commutation circuit;
In each servicesubway, proximity transducer signal acquisition circuit provides suitable driving voltage for the sensor detecting hatch door and landing gear position, and is delivered to DSP minimum system after carrying out pre-process to the sensor signal collected; Folding and unfolding handle signal acquisition circuit is responsible for gathering " in the receipts " of folding and unfolding handle or " putting down " instruction and is delivered to DSP minimum system; The information that DSP minimum system synthetical collection arrives, resolves rear output command to output driving circuit.Cross channel data link is for transmitting voting information; Commutation circuit is used for fault handling, and adopt analog switch to realize, default conditions use a servicesubway; When this passage breaks down, disengagement failure passage, enables another back-up job passage, when two servicesubways all break down, cuts off the output of undercarriage control controller.Output driving circuit produces driving voltage, drives electromagnetic valve to complete the draw-in and draw-off function of alighting gear.
The advantage that the present invention has and beneficial effect are: the present invention adopts electrical dual-redundancy to control, and select dsp chip as processor chips, and undercarriage control control system can be made more to simplify, and reliability is higher, and inverse amplification factor is convenient to realize and adjustment.Because undercarriage control controller adopts two redundant configurations, primary fault work, twice fail-safe fault-tolerant ability can be realized.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is DSP minimum system schematic circuit diagram.
Detailed description of the invention
The two redundancy digital type undercarriage control controller of a kind of aircraft, comprise the servicesubway of two remainings each other, each servicesubway comprises proximity transducer signal acquisition circuit, handle signal acquisition circuit, DSP minimum system and output driving circuit, two DSP minimum systems are connected by cross channel data link, commutation circuit is connected with two DSP minimum systems, two output driving circuits respectively, and output driving circuit is connected with one of two DSP minimum systems and commutation circuit.
In each servicesubway, the function of proximity transducer signal acquisition circuit provides pumping signal to proximity transducer 1 and proximity transducer 2, and receive the signal that proximity transducer 1 and proximity transducer 2 feed back, by the process of modulate circuit, after converting the discrete magnitude signal of 0 to 13V to, be delivered to the DSP minimum system of respective channel, sensor signal conditioning circuit adopts MA17 special chip, when the proximity transducer of target and respective channel is in " close " state, modulate circuit exports 0V, when target and proximity transducer be in " away from " state time, modulate circuit exports 13V.
Folding and unfolding handle signal acquisition circuit is responsible for gathering " in the receipts " of folding and unfolding handle or " putting down " instruction and is delivered to DSP minimum system; The function of handle signal acquisition circuit is the discrete magnitude signal gathering folding and unfolding handle, signal is ground/open form formula, corresponding " in receipts " or " putting down " instruction respectively, handle signal acquisition circuit adopts light-coupled isolation Acquisition Circuit, for preventing the signal of two passages from interacting, after the process of handle signal acquisition circuit, be delivered to the DSP minimum system of respective channel, to being 0V after the ground alignment processing of handle signal, handle signal open alignment processing after be 5V.
The information that DSP minimum system synthetical collection arrives, resolves rear output command to output driving circuit.See Fig. 2, DSP minimum system is primarily of microprocessor, clock circuit, power circuit, watchdog circuit and BIT circuit composition, wherein, microprocessor is for receiving various incoming signal, and calculate folding and unfolding control signal according to current DSP minimum system state and pre-loaded software in DSP minimum system, deliver to output driving circuit and commutation circuit, the DSP minimum system of each passage adopts DSP320F240 chip to make microprocessor, highway width 16, dominant frequency 20M, and expansion has program store 128KB and random access memory 64KB, and failure data storage 8KB, clock circuit provides 20M crystal oscillator to DSP minimum system, power circuit realizes the conversion of various voltage and DSP minimum system to the requirement of the order that powers on, watchdog circuit is used for the mode of operation of monitoring microprocessor, the DSP minimum system of each passage is provided with watchdog circuit, software is monitored by a house dog timing circuit, every 50ms " feeds dog " once by software, if do not had " feeding dog " more than 150ms, house dog timing will be overflowed, produce reseting pulse signal to microprocessor, microprocessor is made to produce hot reset, program is got back to initial point and is brought into operation, start hot reset counting machine simultaneously, when this counting machine reaches 10 times, export faulty condition to commutation circuit, when counting machine does not reach 10 times, think accidental interference, keep current mode of operation, do not export faulty condition to commutation circuit, BIT circuit is used for the software and hardware mode of operation of monitored control system, and faulty condition is exported, the DSP minimum system of each passage is provided with BIT circuit, BIT module in this circuit and software combines work, the mode of operation of free time to the hardware combinations such as power circuit, proximity transducer signal acquisition circuit, microprocessor, output driving circuit of each passage run at normal control program carries out the BIT test of periodically (or order startup formula), and whether the work of check circuit is normal.When being checked through hardware circuit fault, mode by hardware or software is arranged faulty condition and faulty condition is outputted to commutation circuit by BIT circuit or BIT software, the DSP minimum system of each passage is the core control part of the two redundancy digital type undercarriage control controller of aircraft, its radical function receives various incoming signal, and calculate folding and unfolding control signal according to current DSP minimum system state and pre-loaded software in DSP minimum system, deliver to output driving circuit and commutation circuit, software in microprocessor carries out working out and have passed test according to the folding and unfolding control logic of undercarriage and undercarriage door.Cross channel data link is for transmitting voting information; Shared the proximity transducer information and folding and unfolding handle information that receive by cross channel data link between DSP minimum system 1 and DSP minimum system 2, cross channel data link is realized by dual port RAM, simultaneously, the fault status information of the DSP minimum system of each passage is sent to the other side, when DSP minimum system 1 and DSP minimum system 2 all normally work, the DSP minimum system of each passage can utilize proximity transducer information and the folding and unfolding handle information of two remaining, during arbitrary channel failure, remaining is demoted.
Commutation circuit is used for fault handling, and adopt analog switch to realize, default conditions use a servicesubway; When this passage breaks down, disengagement failure passage, enables another back-up job passage, when two servicesubways all break down, cuts off the output of undercarriage control controller, can realize primary fault work, twice fail-safe fault-tolerant ability.Namely start working after commutation circuit powers on, not by the impact of two passage remaining information, commutation circuit receives the fault status information of the output activation bit of two passages and the DSP minimum system of two passages, commutation circuit adopts EPLD to realize, commutation circuit receives the fault status information of the output activation bit of two passages and the DSP minimum system of two passages, when DSP minimum system 1 and DSP minimum system 2 all normally work, commutation circuit controls a wherein road and outputs to electromagnetic valve, when DSP minimum system 1 normally works, during DSP minimum system 2 fault, the output driving circuit of commutation circuit control DSP minimum system 1 place passage outputs to electromagnetic valve, when DSP minimum system 1 fault, when DSP minimum system 2 normally works, the output driving circuit of commutation circuit control DSP minimum system 2 place passage outputs to electromagnetic valve, when DSP minimum system 1 and DSP minimum system 2 all fault time, commutation circuit controls to output to electromagnetic valve without any information, primary fault work can be realized, twice fail-safe fault-tolerant ability.
Output driving circuit produces driving voltage, drives electromagnetic valve to complete the draw-in and draw-off function of alighting gear.The driving element of output driving circuit adopts BTS power drive pipe; outgoing current can reach 5A; this driving tube has the functions such as power control, open circuit/short-circuit detecting, overcurrent protection, feedback of status, the counter potential interference produced when the output signal of output driving circuit adds flywheel diode suppression electromagnetic valve load power down.
Claims (2)
1. the two redundancy digital type undercarriage control controller of aircraft, it is characterized in that, native system comprises the servicesubway of two remainings each other, each servicesubway comprises proximity transducer signal acquisition circuit, handle signal acquisition circuit, DSP minimum system and output driving circuit, two DSP minimum systems are connected by cross channel data link, commutation circuit is connected with two DSP minimum systems, two output driving circuits respectively, and output driving circuit is connected with one of two DSP minimum systems and commutation circuit;
In each servicesubway, proximity transducer signal acquisition circuit provides suitable driving voltage for the sensor detecting hatch door and landing gear position, and is delivered to DSP minimum system after carrying out pre-process to the sensor signal collected; Folding and unfolding handle signal acquisition circuit is responsible for gathering " in the receipts " of folding and unfolding handle or " putting down " instruction and is delivered to DSP minimum system; The information that DSP minimum system synthetical collection arrives, resolves rear output command to output driving circuit; Cross channel data link is for transmitting voting information; Commutation circuit is used for fault handling, and adopt analog switch to realize, default conditions use a servicesubway; When this passage breaks down, disengagement failure passage, enables another back-up job passage, when two servicesubways all break down, cuts off the output of undercarriage control controller; Output driving circuit produces driving voltage, drives electromagnetic valve to complete the draw-in and draw-off function of alighting gear.
2. the two redundancy digital type undercarriage control controller of a kind of aircraft as claimed in claim 1, it is characterized in that, DSP minimum system is primarily of microprocessor, clock circuit, power circuit, watchdog circuit and BIT circuit composition, wherein, microprocessor is for receiving various incoming signal, and calculate folding and unfolding control signal according to current DSP minimum system state and pre-loaded software in DSP minimum system, deliver to output driving circuit and commutation circuit, clock circuit provides 20M crystal oscillator to DSP minimum system, power circuit realizes the conversion of various voltage and DSP minimum system to the requirement of the order that powers on, watchdog circuit is used for the mode of operation of monitoring microprocessor, BIT circuit is used for the software and hardware mode of operation of monitored control system, and faulty condition is exported.
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| CN201310603629.0A CN104648660A (en) | 2013-11-22 | 2013-11-22 | Airplane dual-redundancy digital type undercarriage retraction/extension controller |
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| CN201310603629.0A CN104648660A (en) | 2013-11-22 | 2013-11-22 | Airplane dual-redundancy digital type undercarriage retraction/extension controller |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105334759A (en) * | 2015-11-25 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Control method for loading signals of main wheels of airplane |
| CN106094629A (en) * | 2016-06-28 | 2016-11-09 | 北京安控科技股份有限公司 | A kind of two functional safety controllers taking a framework |
| CN106567420A (en) * | 2016-07-26 | 2017-04-19 | 中国航空工业集团公司西安飞行自动控制研究所 | Triple-redundancy software control system of electrical transmission control excavator |
| CN106707792A (en) * | 2016-11-18 | 2017-05-24 | 中航飞机起落架有限责任公司 | Multifunctional undercarriage integration test control device and method |
| CN106873616A (en) * | 2015-12-11 | 2017-06-20 | 中国航空工业第六八研究所 | A kind of decision method of the flight control system state of ground |
| CN107450307A (en) * | 2017-08-30 | 2017-12-08 | 陕西千山航空电子有限责任公司 | A kind of double remaining control methods of undercarriage of Electromechanical Management computer |
| GB2562027A (en) * | 2017-03-02 | 2018-11-07 | Airbus Operations Ltd | Control system and method for landing gear extension/retraction |
| CN108776489A (en) * | 2018-04-11 | 2018-11-09 | 南安市创培电子科技有限公司 | A kind of control method of unmanned plane tripod |
| CN108820250A (en) * | 2018-06-19 | 2018-11-16 | 中航飞机起落架有限责任公司 | A kind of undercarriage vacant lot condition checkout gear |
| CN109343335A (en) * | 2018-11-05 | 2019-02-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of hatch door redundance control system |
| CN109823522A (en) * | 2017-11-23 | 2019-05-31 | 成都凯天电子股份有限公司 | Multi-redundant undercarriage electric retractable controller |
| CN111261458A (en) * | 2020-03-08 | 2020-06-09 | 陕西航空电气有限责任公司 | Contactor control method adopting non-similar dual processors in aviation power distribution system |
| CN112748751A (en) * | 2020-12-22 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Digital airplane environment control system and method |
| CN114442521A (en) * | 2021-12-29 | 2022-05-06 | 中国航空工业集团公司西安航空计算技术研究所 | Cross control circuit between dual-redundancy signal channels |
| US11541992B2 (en) * | 2019-02-28 | 2023-01-03 | Airbus Operations Limited | Landing gear retraction |
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Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105334759B (en) * | 2015-11-25 | 2019-02-12 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft main wheel carrying signal control method |
| CN105334759A (en) * | 2015-11-25 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Control method for loading signals of main wheels of airplane |
| CN106873616A (en) * | 2015-12-11 | 2017-06-20 | 中国航空工业第六八研究所 | A kind of decision method of the flight control system state of ground |
| CN106094629A (en) * | 2016-06-28 | 2016-11-09 | 北京安控科技股份有限公司 | A kind of two functional safety controllers taking a framework |
| CN106094629B (en) * | 2016-06-28 | 2019-06-21 | 北京安控科技股份有限公司 | A kind of two take the functional safety controller of a framework |
| CN106567420A (en) * | 2016-07-26 | 2017-04-19 | 中国航空工业集团公司西安飞行自动控制研究所 | Triple-redundancy software control system of electrical transmission control excavator |
| CN106707792A (en) * | 2016-11-18 | 2017-05-24 | 中航飞机起落架有限责任公司 | Multifunctional undercarriage integration test control device and method |
| CN106707792B (en) * | 2016-11-18 | 2019-07-19 | 中航飞机起落架有限责任公司 | A kind of comprehensive joint-trial control method of multi-functional undercarriage |
| GB2562027A (en) * | 2017-03-02 | 2018-11-07 | Airbus Operations Ltd | Control system and method for landing gear extension/retraction |
| CN107450307A (en) * | 2017-08-30 | 2017-12-08 | 陕西千山航空电子有限责任公司 | A kind of double remaining control methods of undercarriage of Electromechanical Management computer |
| CN109823522B (en) * | 2017-11-23 | 2024-02-23 | 成都凯天电子股份有限公司 | Multi-redundancy undercarriage electric retraction controller |
| CN109823522A (en) * | 2017-11-23 | 2019-05-31 | 成都凯天电子股份有限公司 | Multi-redundant undercarriage electric retractable controller |
| CN108776489A (en) * | 2018-04-11 | 2018-11-09 | 南安市创培电子科技有限公司 | A kind of control method of unmanned plane tripod |
| CN108820250B (en) * | 2018-06-19 | 2020-10-02 | 中航飞机起落架有限责任公司 | Undercarriage open ground state detection device |
| CN108820250A (en) * | 2018-06-19 | 2018-11-16 | 中航飞机起落架有限责任公司 | A kind of undercarriage vacant lot condition checkout gear |
| CN109343335A (en) * | 2018-11-05 | 2019-02-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of hatch door redundance control system |
| US11541992B2 (en) * | 2019-02-28 | 2023-01-03 | Airbus Operations Limited | Landing gear retraction |
| CN111261458A (en) * | 2020-03-08 | 2020-06-09 | 陕西航空电气有限责任公司 | Contactor control method adopting non-similar dual processors in aviation power distribution system |
| CN111261458B (en) * | 2020-03-08 | 2022-06-07 | 陕西航空电气有限责任公司 | Contactor control method adopting non-similar dual processors in aviation power distribution system |
| CN112748751A (en) * | 2020-12-22 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Digital airplane environment control system and method |
| CN114442521A (en) * | 2021-12-29 | 2022-05-06 | 中国航空工业集团公司西安航空计算技术研究所 | Cross control circuit between dual-redundancy signal channels |
| CN114442521B (en) * | 2021-12-29 | 2024-03-19 | 中国航空工业集团公司西安航空计算技术研究所 | Cross control circuit between dual-redundancy signal channels |
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Application publication date: 20150527 |