CN104714450A - Redundancy management algorithm of mechanical dual-redundancy and electrical triplex redundancy atmosphere data sensor - Google Patents
Redundancy management algorithm of mechanical dual-redundancy and electrical triplex redundancy atmosphere data sensor Download PDFInfo
- Publication number
- CN104714450A CN104714450A CN201510103091.6A CN201510103091A CN104714450A CN 104714450 A CN104714450 A CN 104714450A CN 201510103091 A CN201510103091 A CN 201510103091A CN 104714450 A CN104714450 A CN 104714450A
- Authority
- CN
- China
- Prior art keywords
- air data
- data sensor
- sensor
- redundancy
- normal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0428—Safety, monitoring
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24193—Two transducers for same parameter
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/26—Pc applications
- G05B2219/2612—Data acquisition interface
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Safety Devices In Control Systems (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The invention provides a redundancy management algorithm of a mechanical dual-redundancy and electrical triplex redundancy atmosphere data sensor. When the output result of an atmosphere data sensor A is the same as the output result of a sensor B which is from the same mechanical equipment with the sensor A, and the output result of the sensor A is different from the output result of an atmosphere data sensor C which is from another mechanical equipment, the sensor A, the sensor B and the sensor C are subjected to self-test, the sensor A and the sensor B are regarded as the same output for judging fault safety value, then the sensor C is combined for judging the data fault of the mechanical equipment, and the redundancy management that in a traditional 2:1 way, the different data are cut off is avoided, so that the judgment of the data output results of the sensors is more accurate.
Description
Technical field
The invention belongs to aircraft flight control system technical field, particularly relate to Aircraft Management System redundance signal redundancy management policing issue.
Background technology
Air data sensor is the important parameter survey sensor of flight control system and Aircraft Management System, and its Core Feature is that complete, the static pressure air pressure signal of input are converted to digital signal and calculate output.Air data sensor based on total head, static pressure (if need revise, then use revised static pressure) calculate the atmospheric parameters such as dynamic pressure, static pressure, barometer altitude, calibrated airspeed, rising or falling speed, Mach number, export to other system on Aircraft Management Computer and machine.
In correlation technique, during remaining electric triplex redundance air data sensor redundancy management two for machinery, because wherein two sensor source are from same plant equipment A, another one sensor connects mechanical equipment B, and the gas circuit between A, B is not communicated with.If the mechanical faults such as airway blockage appear in A, and B normally works, and will cause triplex redundance policing algorithm that the sensor signal of A equipment is judged as fault-signal, will cause by mistake cutting correct signal like this.
Summary of the invention
For overcoming Problems existing in correlation technique, the invention provides the two remaining electric triplex redundance air data sensor Systems Redundancy Management of a kind of machinery, for two remaining gas circuits of some aircraft air data systems and the remaining mismatch problem of triplex redundance air data sensor, realize the redundancy management of atmosphere data information in particular cases.
The two remaining electric triplex redundance air data sensor Systems Redundancy Management of machinery of the present invention, when the air data sensor A wherein from same plant equipment is identical with sensor B Output rusults, and time different from the Output rusults of the air data sensor C from another plant equipment, Autonomous test is carried out to A, B, C tri-sensors, carries out sensor redundancy management in the following manner:
A) when C air data sensor is from monitor for faults, and A, B two air data sensor Autonomous test signals have at least a road normal, then judge C air data sensor signal fault, the equipment be connected with A, B two air data sensors is normal;
B) when C air data sensor is normal from monitoring, and A, B two air data sensor Autonomous test signal total failures, then judge that the event of C air data sensor signal is normal, the equipment failure be connected with A, B two air data sensors;
C) when C air data sensor is normal from monitoring, and A, B two air data sensor Autonomous test signals have at least a road normal, then complete resection, puts failure safe value, carry out signal reconstruction.
Preferably, when C air data sensor is from monitor for faults, and A, B two air data sensor Autonomous test signals are all normal, export the average of A, B two air data sensors.
In above-mentioned either a program preferably, described air data sensor receives from the switching value of the startup self-inspection of Aircraft Management Computer and voltage analog and the digital quantity of stagnation pressure signal is transferred to described Aircraft Management Computer.。
Technical scheme provided by the invention comprises following beneficial effect: the two remaining electric triplex redundance sensor Systems Redundancy Management of machinery provided by the invention is by the algorithm management again to three-way sensor, the mode avoiding traditional 2:1 cuts away the redundancy management of different pieces of information, makes the judgement of the output data result of sensor more accurate.
Accompanying drawing explanation
Fig. 1 is cross-linked block diagram according to the air data sensor of a preferred embodiment of the two remaining electric triplex redundance air data sensor Systems Redundancy Management of the present invention's machinery.
Monitoring strategies schematic diagram when Fig. 2 is atmosphere data information 2:1 embodiment illustrated in fig. 1.
Embodiment
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.
Atmosphere data information of the present invention carries out redundancy management signal behavior according to three signal monitoring voting algorithms.
As shown in Figure 1, intermediate standard pitot gas circuit connects two air data sensors, and left side pitot gas circuit connects an air data sensor, and the gas circuit between middle pitot and left side pitot is not communicated with.If the mechanical faults such as airway blockage appear in middle pitot, and left side pitot normally works, will cause triplex redundance policing algorithm that the air data sensor signal that left side pitot connects is judged as fault-signal, will by mistake cutting correct signal be caused like this.
For slowing down the degradation speed of atmosphere data information, require to occur that (2 is two air data sensor information from middle pitot to 2:1 fault when triplex redundance atmosphere data information compares monitoring, 1 is the air data sensor information from left side pitot) time, binding signal from monitor message, (namely whether the state matrix of each signal is 11,11 representatives are normal), by following algorithms selection useful signal, as shown in Figure 2:
A) air data sensor connected when left front pitot is from monitor for faults, and two air data sensor Autonomous test signals that head pitot connects have at least a road normal, then think that two air data sensor signals that head pitot connects are normal, the air data sensor signal fault that left front pitot connects;
B) air data sensor connected when left front pitot is monitored normal certainly, and two air data sensor Autonomous test signal total failures that head pitot connects, the air data sensor then sentencing the connection of left front pitot is normal, two air data sensor signal faults that head pitot connects;
C) air data sensor connected when left front pitot is monitored normal certainly, and two air data sensor Autonomous test signals that head pitot connects have one at least normally, then complete resection, puts failure safe value, carry out signal reconstruction.
When C air data sensor is from monitor for faults, and A, B two air data sensor Autonomous test signals are all normal, export the average of A, B two air data sensors.
In the present embodiment, described air data sensor receives from the switching value of the startup self-inspection of Aircraft Management Computer and voltage analog and the digital quantity of stagnation pressure signal is transferred to described Aircraft Management Computer.
It should be noted that; the two remaining electric triplex redundance sensor Systems Redundancy Management of the present invention's machinery comprises any one and combination in any thereof in above-described embodiment; but embodiment recited above is only be described the preferred embodiment of the present invention; not the scope of the invention is limited; do not departing under the present invention designs spiritual prerequisite; the various distortion that the common engineering technical personnel in this area make technical scheme of the present invention and improvement, all should fall in protection domain that claims of the present invention determine.
Claims (3)
1. the two remaining electric triplex redundance air data sensor Systems Redundancy Management of machinery, it is characterized in that: when the air data sensor A wherein from same plant equipment is identical with sensor B Output rusults, and time different from the Output rusults of the air data sensor C from another plant equipment, Autonomous test is carried out to A, B, C tri-sensors, carries out sensor redundancy management in the following manner:
A) when C air data sensor is from monitor for faults, and A, B two air data sensor Autonomous test signals have at least a road normal, then judge C air data sensor signal fault, the equipment be connected with A, B two air data sensors is normal;
B) when C air data sensor is normal from monitoring, and A, B two air data sensor Autonomous test signal total failures, then judge that the event of C air data sensor signal is normal, the equipment failure be connected with A, B two air data sensors;
C) when C air data sensor is normal from monitoring, and A, B two air data sensor Autonomous test signals have at least a road normal, then complete resection, puts failure safe value, carry out signal reconstruction.
2. the two remaining electric triplex redundance air data sensor Systems Redundancy Management of machinery according to claim 1, it is characterized in that: when C air data sensor is from monitor for faults, and A, B two air data sensor Autonomous test signals are all normal, export the average of A, B two air data sensors.
3. the two remaining electric triplex redundance air data sensor Systems Redundancy Management of machinery according to claim 2, is characterized in that: described air data sensor receives from the switching value of the startup self-inspection of Aircraft Management Computer and voltage analog and the digital quantity of stagnation pressure signal is transferred to described Aircraft Management Computer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510103091.6A CN104714450B (en) | 2015-03-09 | 2015-03-09 | A kind of electric triplex redundance air data sensor Systems Redundancy Management of double remainings of machinery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510103091.6A CN104714450B (en) | 2015-03-09 | 2015-03-09 | A kind of electric triplex redundance air data sensor Systems Redundancy Management of double remainings of machinery |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104714450A true CN104714450A (en) | 2015-06-17 |
| CN104714450B CN104714450B (en) | 2017-11-03 |
Family
ID=53413882
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510103091.6A Active CN104714450B (en) | 2015-03-09 | 2015-03-09 | A kind of electric triplex redundance air data sensor Systems Redundancy Management of double remainings of machinery |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104714450B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105334845A (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 | Incidence angle redundancy management method for mechanical dual-redundancy and electrical four-redundancy |
| CN106200527A (en) * | 2016-08-12 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of airborne air data system data capture method based on double remainings |
| CN106468883A (en) * | 2015-08-20 | 2017-03-01 | 陕西千山航空电子有限责任公司 | A kind of trainer aircraft Electromechanical Management device |
| CN106483977A (en) * | 2016-11-30 | 2017-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of redundance flight control system and control method |
| CN106950002A (en) * | 2017-02-24 | 2017-07-14 | 中国航天空气动力技术研究院 | A kind of Flush Airdata Sensing System |
| CN108375780A (en) * | 2018-03-02 | 2018-08-07 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of redundancy management method of triplex redundance GPS signal |
| CN109187896A (en) * | 2018-08-06 | 2019-01-11 | 大连理工大学 | A kind of module combined type multi-parameter water quality data acquisition device and its application method |
| CN110514266A (en) * | 2019-06-27 | 2019-11-29 | 杭州洛通智能设备有限公司 | A kind of method and device of dual-redundancy switch type sensor voting |
| CN112046783A (en) * | 2020-07-31 | 2020-12-08 | 苏州千诚锐创机器人科技有限公司 | Flight control method and system of three-IMU redundancy technology |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003028823A (en) * | 2001-07-18 | 2003-01-29 | Honda Motor Co Ltd | Signal processing device |
| CN202213715U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Multi-power configuration of hydraulic energy system of civil airplane |
| CN103869781A (en) * | 2014-03-14 | 2014-06-18 | 北京航空航天大学 | Non-similar three-redundancy onboard electric load management center |
| CN104199440A (en) * | 2014-08-20 | 2014-12-10 | 中国运载火箭技术研究院 | Four-unit three-bus redundancy heterogeneous GNC (guidance navigation control) system |
-
2015
- 2015-03-09 CN CN201510103091.6A patent/CN104714450B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003028823A (en) * | 2001-07-18 | 2003-01-29 | Honda Motor Co Ltd | Signal processing device |
| CN202213715U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Multi-power configuration of hydraulic energy system of civil airplane |
| CN103869781A (en) * | 2014-03-14 | 2014-06-18 | 北京航空航天大学 | Non-similar three-redundancy onboard electric load management center |
| CN104199440A (en) * | 2014-08-20 | 2014-12-10 | 中国运载火箭技术研究院 | Four-unit three-bus redundancy heterogeneous GNC (guidance navigation control) system |
Non-Patent Citations (1)
| Title |
|---|
| 郭偶凡: "三余度光传飞控总线配置及实现技术研究", 《中国优秀硕士学位论文全文数据库(电子期刊)工程科技II辑》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106468883A (en) * | 2015-08-20 | 2017-03-01 | 陕西千山航空电子有限责任公司 | A kind of trainer aircraft Electromechanical Management device |
| CN105334845A (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 | Incidence angle redundancy management method for mechanical dual-redundancy and electrical four-redundancy |
| CN105334845B (en) * | 2015-11-25 | 2020-05-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Mechanical dual-redundancy electrical four-redundancy angle-of-attack redundancy management method |
| CN106200527A (en) * | 2016-08-12 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of airborne air data system data capture method based on double remainings |
| CN106483977A (en) * | 2016-11-30 | 2017-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of redundance flight control system and control method |
| CN106950002A (en) * | 2017-02-24 | 2017-07-14 | 中国航天空气动力技术研究院 | A kind of Flush Airdata Sensing System |
| CN108375780A (en) * | 2018-03-02 | 2018-08-07 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of redundancy management method of triplex redundance GPS signal |
| CN109187896A (en) * | 2018-08-06 | 2019-01-11 | 大连理工大学 | A kind of module combined type multi-parameter water quality data acquisition device and its application method |
| CN109187896B (en) * | 2018-08-06 | 2020-06-16 | 大连理工大学 | Module combined type multi-parameter water quality data acquisition device and use method thereof |
| CN110514266A (en) * | 2019-06-27 | 2019-11-29 | 杭州洛通智能设备有限公司 | A kind of method and device of dual-redundancy switch type sensor voting |
| CN112046783A (en) * | 2020-07-31 | 2020-12-08 | 苏州千诚锐创机器人科技有限公司 | Flight control method and system of three-IMU redundancy technology |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104714450B (en) | 2017-11-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104714450A (en) | Redundancy management algorithm of mechanical dual-redundancy and electrical triplex redundancy atmosphere data sensor | |
| CA2972453C (en) | A system and method for monitoring a critical component of an aircraft | |
| JP5473226B2 (en) | Aircraft engine monitoring method | |
| CN109213118B (en) | Control system with triple redundancy for an aircraft and method for managing the same | |
| US7355828B2 (en) | Turbo machinery speed monitor | |
| WO2017118670A3 (en) | Fusion of aviation-related data for comprehensive aircraft system health monitoring | |
| KR101418479B1 (en) | Fly-by-wire flight control system having an integrated ofp function using a flight type identity signal and method for controlling the same | |
| CN106483977A (en) | A kind of redundance flight control system and control method | |
| US10760485B2 (en) | Virtualizing data for a vehicle control system | |
| US20090292951A1 (en) | Method and device for fault location in a system | |
| EP3096196B1 (en) | System and method for diagnosing line replaceable unit failure | |
| CN105137966A (en) | Switch signal output channel detection method and structure | |
| GB2427940A (en) | Turbo machinery speed monitor | |
| US10683101B2 (en) | Method for determining at least one faulty piece of equipment of an aircraft, and corresponding system | |
| US8441375B2 (en) | Aircraft power failure simulation apparatus and method | |
| KR101594413B1 (en) | Real-time monitoring system of station control apparatus and monitoring method thereof | |
| US10823076B2 (en) | Device for monitoring a turbine engine of an aircraft | |
| EP1739438B1 (en) | Turbo machinery speed monitor | |
| CN104361915B (en) | Constant value test system of reactor key process measurement parameters and test method | |
| US11836057B2 (en) | Fault location in a redundant acquisition system | |
| US10712736B2 (en) | Controlling an aircraft comprising a plurality of loadable configuration sever data based on detecting one or more diagnostic test interfaces | |
| CN108087125A (en) | A kind of aero-engine control protective unit and method | |
| RU2371695C1 (en) | Vibration control system | |
| Rouissi et al. | Fault tolerance in wind turbine sensor systems for diagnosability properties guarantee | |
| US20230387676A1 (en) | Industrial control apparatus and monitoring method for industrial control apparatus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |